[PPT] - Select ADO-DG Case Studies in Aerodynamic Design Optimization PowerPoint Presentation

SLIDE 1

Select ADO-DG Case Studies in Aerodynamic Design Optimization Antony Jameson

T. V. Jones Professor of Engineering
Dept. Aeronautics & Astronautics

Stanford University Stanford, CA 94305-3030, USA

John C. Vassberg

Boeing Technical Fellow Advanced Concepts Design Center Boeing Commercial Airplanes Long Beach, CA 90846, USA

Invited Presentation AIAA Sci-Tech Conference Kissimmee, FL 5 January, 2015

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 1

SLIDE 2

OUTLINE

NACA0012-ADO INVISCID AIRFOIL

– ADO-DG Case 1 – SYN83 Optimizations – FLO82 Cross Analyses – GSA Study – Case Summary

ADO-CRM-WING

– ADO-DG Cases 4.1-4.3 – SYN107 Optimizations – Case Summary

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 2

SLIDE 3

NACA0012-ADO MODEL PROBLEM

Optimization Statement

– Minimize Drag – M = 0.85, α = 0◦, Inviscid Flow – Maintain or Exceed Thickness Distribution of Baseline

NACA0012-ADO Airfoil Equation

– Closed Trailing-Edge at x = 1

yA(x) = ±0.12 0.2

0.2969√x − 0.1260x − 0.3516x2 + 0.2843x3 − 0.1036x4

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 3

SLIDE 4

ADO-DG CASE 1: NACA0012-ADO

Optimization Methods

– SYN83 – GSA Design Space Survey

FLO82 Cross-Analysis

– Vassberg & Jameson, “In Pursuit of Grid Convergence for Two-Dimensional Euler Solutions,” AIAA Journal of Aircraft, Vol.47, No.4, pp.1152-1166, July-August, 2010. – High-Quality O-Mesh with Aspect-Ratio-1 Cells – Family of Meshes (32x32)-to-(2048x2048) Cells – Converge Residuals to Machine-Level Zero – Richardson Extrapolation

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 4

SLIDE 5

BASELINE NACA0012-ADO SOLUTION

NACA0012-ADO - JCV AR=1 GRID

MACH 0.850 ALPHA 0.0000000 CL 0.000000000 CD 0.047122638 CM 0.000000000 GRID 2048x 2048 NCYC 500 RED -10.79

1.2 0.8 0.4 0.0

0.4
0.8
1.2
1.6
2.0

CP

++ + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + MACH: MIN 0.0000604 MAX 1.3691850 CONTOURS 0.050

FLO82 Solution for NACA0012-ADO Airfoil at M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 5

SLIDE 6

SYN83 OPTIMIZATION

SYN83 C-mesh (768x128) about NACA0012-ADO.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 6

SLIDE 7

SYN83 OPTIMIZATION

SYN83 Results (Cd in counts). Airfoil Cd ∆Cd Seed NACA0012-ADO 456.34

Design

SYNA 103.71

352.63

Seed SEEDB 101.79

354.55

Design SYNB 79.31

377.03

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 7

SLIDE 8

SYN83 OPTIMIZATION

NADOV01 OPTIMUM AIRFOIL

MACH 0.850 ALPHA 0.0000000 CL 0.000000000 CD 0.011834217 CM 0.000000000 GRID 2048x 2048 NCYC 500

. .

1.2 0.8 0.4 0.0

0.4
0.8
1.2
1.6
2.0

CP

+ + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + MACH: MIN 0.0000631 MAX 1.6034683 CONTOURS 0.060

FLO82 Solution for SYNA Airfoil at M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 8

SLIDE 9

SYN83 OPTIMIZATION

NADOV02 OPTIMUM AIRFOIL

MACH 0.850 ALPHA 0.0000000 CL 0.000000000 CD 0.008449573 CM 0.000000000 GRID 2048x 2048 NCYC 500

. .

1.2 0.8 0.4 0.0

0.4
0.8
1.2
1.6
2.0

CP

+ + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + MACH: MIN 0.0000566 MAX 1.5738200 CONTOURS 0.060

FLO82 Solution for SYNB Airfoil at M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 9

SLIDE 10

FLO82 O-MESH

Close-up view of the NACA0012-ADO 256x256 O-mesh.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 11

SLIDE 11

(256 x 256) (512 x 512)

0.0 100.0 200.0 300.0 400.0 500.0 600.0

Work

16.0
14.0
12.0
10.0
8.0
6.0
4.0
2.0

0.0

Log(Error)

0.2

0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4

Nsup

R R L L D D S S S 0.0 100.0 200.0 300.0 400.0 500.0 600.0

Work

16.0
14.0
12.0
10.0
8.0
6.0
4.0
2.0

0.0

Log(Error)

0.2

0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4

Nsup

R R L L D D S S

FLO82 Convergence Histories at M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 12

SLIDE 12

(1024 x 1024) (2048 x 2048)

0.0 100.0 200.0 300.0 400.0 500.0 600.0

Work

16.0
14.0
12.0
10.0
8.0
6.0
4.0
2.0

0.0

Log(Error)

0.2

0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4

Nsup

R R L L D D S S S 0.0 100.0 200.0 300.0 400.0 500.0 600.0

Work

16.0
14.0
12.0
10.0
8.0
6.0
4.0
2.0

0.0

Log(Error)

0.2

0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4

Nsup

R R L L D D S S

FLO82 Convergence Histories at M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 13

SLIDE 13

FLO82 CROSS-ANALYSIS

FLO82 Drag Assessment (Cd in counts). Airfoil N256 N512 N1024 N2048 ∞ ∆Cd NACA0012-ADO 470.19 470.09 471.13 471.23 471.27

SYNA

153.78 123.24 119.03 118.34 118.21

353.06

SEEDB 111.04 98.98 97.68 96.85 95.42

375.85

SYNB 109.25 86.87 84.68 84.50 84.48

386.79

NADOT101 487.50 488.20 488.48 488.58 488.62 +17.35 SYNBT101 122.22 99.20 96.75 96.64 96.63

374.64

Note: 1% Increase in Thickness Increases Drag:

NACA0012-ADO Airfoil by 3.68%
SYNB Design by 14.38%.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 14

SLIDE 14

CARRIER-DESTERAC AIRFOIL (G)

CARRIER-DESTARAC BEZ96FP OPTIMUM AIRFOIL

MACH 0.850 ALPHA 0.0000000 CL 0.000000000 CD 0.003589230 CM 0.000000000 GRID 2048x 2048 NCYC 500 RED -3.70 XCP 0.000000000 YCP 0.000000000

. .

1.2 0.8 0.4 0.0

0.4
0.8
1.2
1.6
2.0

CP

+ + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + ++ + + + + + + + + + + + + + +++ ++ + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + MACH: MIN 0.0000687 MAX 1.6421540 CONTOURS 0.060

FLO82 Solution, Carrier-Desterac Airfoil (G), M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 15

SLIDE 15

BISSON-NADARAJAH AIRFOIL (S)

SIVAFOIL OPTIMUM AIRFOIL

MACH 0.850 ALPHA 0.0000000 CL 0.000000000 CD 0.004655680 CM 0.000000000 GRID 2048x 2048 NCYC 500 RED -4.65

.

1.2 0.8 0.4 0.0

0.4
0.8
1.2
1.6
2.0

CP

+ + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + ++ + + + + + + + + + + + + + + + + + + + + ++ + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + MACH: MIN 0.0001408 MAX 1.7579063 CONTOURS 0.070

FLO82 Solution, Bisson-Nadarajah Airfoil (S), M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 16

SLIDE 16

CARY AIRFOIL (A)

ANDREW CARY OPTIMUM AIRFOIL

MACH 0.850 ALPHA 0.0000000 CL 0.000000000 CD 0.004014639 CM 0.000000000 GRID 2048x 2048 NCYC 500 RED -5.99

. .

1.2 0.8 0.4 0.0

0.4
0.8
1.2
1.6
2.0

CP

+ + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + MACH: MIN 0.0000373 MAX 1.6728016 CONTOURS 0.060

FLO82 Solution, Cary Airfoil (A), M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 17

SLIDE 17

GSA STUDY

GSA Sub-Space Spanned By 3 Airfoils

– Gerald’s, Siva’s & Andrew’s Optimimum Airfoils

Geometric RMS Distances Between GSA Airfoils

– GS: 0.0258890 – GA: 0.0328760 – SA: 0.0096097

GSA Triangle Interior Angles

–

G:

12.9886◦ –

S:

129.7516◦ –

A:

37.2598◦

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 18

SLIDE 18

A-Airfoil S-Airfoil G-Airfoil GSA Triangle & FLO82 Survey Locations.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 19

SLIDE 19

GSA FLO82 Results, M = 0.85, α = 0◦. GW T SW T AW T Cd∞ XT RI YT RI A 0.00 0.00 1.00 39.189621 0.03203 0.00739 0.00 0.25 0.75 ∼37.0 0.03050 0.00554 0.00 0.50 0.50 ∼37.0 0.02896 0.00369 0.00 0.75 0.25 40.531373 0.02743 0.00185 S 0.00 1.00 0.00 45.656136 0.02589 0.00000 0.25 0.00 0.75 43.724493 0.02403 0.00554 0.25 0.25 0.50 39.300977 0.02249 0.00369 0.25 0.50 0.25 40.930957 0.02095 0.00185 0.25 0.75 0.00 44.367019 0.01942 0.00000 0.50 0.00 0.50 44.688405 0.01602 0.00369 0.50 0.25 0.25 41.051787 0.01448 0.00185 0.50 0.50 0.00 42.651239 0.01294 0.00000 0.75 0.00 0.25 39.288289 0.00801 0.00185 0.75 0.25 0.00 37.520335 0.00647 0.00000 0.90 0.00 0.10 34.978658 0.00320 0.00074 * 0.90 0.10 0.00 33.911086 0.00259 0.00000 0.95 0.00 0.05 34.777423 0.00160 0.00037 0.95 0.05 0.00 34.142484 0.00130 0.00000 G 1.00 0.00 0.00 35.818186 0.00000 0.00000 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 20

SLIDE 20

GSA FLO82 Solutions, Iso-A Contours, M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 21

SLIDE 21

GSA FLO82 Solutions, Iso-S Contours, M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 22

SLIDE 22

FLO82 Solutions, M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 23

SLIDE 23

FLO82 Solutions, Level View of Valley, M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 24

SLIDE 24

FLO82 Solutions, Elevated View of Valley, M = 0.85, α = 0◦.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 25

SLIDE 25

ADO-DG CASE-1 SUMMARY

Optimizations Yield Pathological Designs

– Small Geometric Changes ⇒ Large Solution Deltas

Non-Unique Solutions at Design Point

– Lifting (±) Solutions for Symmetric Airfoils at α = 0◦

Convergence Issues with Flow & Adjoint Solvers

– Forcing Symmetric Solutions Helps

Shock-Free Design Still Not Found

– The GSA Airfoils Are Close

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 26

SLIDE 26

ADO-CRM-WING MODEL PROBLEM

ADO-DG Case 4 General Statement

– Minimize Drag at Fixed Lifting Condition(s) – Re = 5.0 × 106 – CM ≥ −0.17 at CL = 0.50 & M = 0.85 – Maintain or Exceed Internal Volume of Baseline Wing

Case 4.1 Single-Point

– M = 0.85, CL = 0.50

Case 4.2 Triple-Point CL Sweep

– M = 0.85, CL = [0.45 , 0.50 , 0.55], WT = [1 , 2 , 1]

Case 4.3 Triple-Point Mach Sweep

– M = [0.84 , 0.85 , 0.86], CL = 0.50, WT = [1 , 2 , 1]

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 27

SLIDE 27

ADO-CRM-WING MODEL PROBLEM

ADO-CRM-Wing Reference Quantities

– Sref/2 = 3.407014, Cref = 1.0, b/2 = 3.75820 – Xref = 1.2077, Y ref = 0.0, Zref = 0.007669

SYN107 Optimizations

– Constrained Lifting Condition(s)

Active Adjustment of α During Convergence
Includes dCD/dCL Terms in Gradient Formulation

– Added Pitching-Moment Penalty

Sufficient to Achieve CM Constraint

– Constrained Airfoil Area Distribution

Over-Constraint on Wing Volume
More Representative of Practice

– Omits Eddy Viscousity Derivatives

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 28

SLIDE 28

SYN107 OPTIMIZATIONS

SYN107 Optimization Require ∼ 2.3 Hours

– Per Design Point, Per 100 Design Cycles – 2046 Design Variables; (2x31x33) Cubic B-Spline CPs – Initial & Every 10th Design Cycle

240 Iters for Analysis
160 Iters for dCD/dCL, dCM/dCL & dCL/dα
240 Iters for Adjoint

– Otherwise

20 Iters for Analysis & Adjoint
SYN107 Analyses Require ∼ 4.2 Minutes

– Per Flow Condition (200 Iters) – Run as Alpha or Mach Sweeps – Grid: (256x64x48) C-Mesh

Parallel Execution on 4 Cores Deskside Computer

– Intel i7-970 CPU at 3.2 GHz; 2011-Q1

Current Computers ∼ 5X Faster

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 29

SLIDE 29

ADO-DG CASE 4: BASELINE WING

Design Pt.: M = 0.85, CL = 0.50, Re = 5.0×106
Polar:

CL = [0.45 , 0.50 , 0.55]

DragRise:

M = [0.84 , 0.85 , 0.86]

Comparisons

– Overlaid Pressure Distributions

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 30

SLIDE 30

SYMBOL SOURCE

Baseline Baseline Baseline

ALPHA

1.816 2.196 2.552

CL

0.4497 0.5011 0.5513

CD

0.01905 0.02155 0.02453

CM

0.16701
0.18517
0.20390

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION

REN = 5.00 , MACH = 0.850

John C. Vassberg 17:48 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 31

SLIDE 31

SYMBOL SOURCE

Baseline Baseline Baseline

MACH

0.840 0.850 0.860

ALPHA

2.299 2.196 2.085

CL

0.5008 0.5011 0.5013

CD

0.02096 0.02155 0.02257

CM

0.18138
0.18517
0.19136

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION

REN = 5.00

John C. Vassberg 18:27 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 32

SLIDE 32

ADO-DG CASE 4.1: Single-Point

M = 0.85, CL = 0.50, Re = 5.0 × 106
Design Cycle Histories

– Drag & Pitching Moment

Baseline .vs. Final Design Comparisons

– Overlaid Pressure Distributions – Side-by-Side Upper-Surface Isobars – Overlaid Spanload Distributions

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 33

SLIDE 33

0.0202 0.0204 0.0206 0.0208 0.0210 0.0212 0.0214 0.0216 10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.5 , Ren = 5 million

ADODG-CRM CASE 4.1 DRAG HISTORY SYN107 Optimizations Design Cycle Drag Coefficient , CD

Case 4.1 Opt

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 34

SLIDE 34

0.165
0.170
0.175
0.180
0.185
0.190

10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.5 , Ren = 5 million

ADODG-CRM CASE 4.1 PITCHING-MOMENT HISTORY SYN107 Optimizations Design Cycle Pitching-Moment Coefficient , CMP

Case 4.1 Opt

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 35

SLIDE 35

SYMBOL SOURCE

Baseline Case 4.1 Opt

ALPHA

2.196 2.729

CL

0.5011 0.4983

CD

0.02155 0.02055

CM

0.18517
0.16695

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.1 OPTIMIZATION

REN = 5.00 , MACH = 0.850

John C. Vassberg 17:34 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 36

SLIDE 36

COMPARISON OF UPPER SURFACE CONTOURS ADODG-CRM CASE 4.1 OPTIMIZATION

REN = 5.00 , MACH = 0.850 ( Contours at 0.05 Cp )

Solution 1: Baseline ALPHA = 2.20 , CL = 0.5011 CD = 0.02155 Solution 2: Case 4.1 Opt ALPHA = 2.73 , CL = 0.4983 CD = 0.02055

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 37

SLIDE 37

10 20 30 40 50 60 70 80 90 100 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 SPANLOAD & SECT CL PERCENT SEMISPAN

C*CL/CREF CL

SYMBOL SOURCE

Baseline Case 4.1 Opt

ALPHA

2.196 2.729

CL

0.5011 0.4983

CD

0.02155 0.02055

CM

0.18517
0.16695

COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.1 OPTIMIZATION

REN = 5.00 , MACH = 0.850

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 38

SLIDE 38

ADO-DG CASE 4.2: Triple-Point CL

M = 0.85, CL = [0.45 , 0.50 , 0.55], Re = 5.0×106
Design Cycle Histories, All 3 Conditions

– Drag & Pitching Moment

Baseline .vs. Final Design Comparisons

– Overlaid Pressure Distributions – Overlaid Spanload Distributions

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 39

SLIDE 39

0.0185 0.0186 0.0187 0.0188 0.0189 0.0190 0.0191 10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.45 , Ren = 5 million

ADODG-CRM CASE 4.2a DRAG HISTORY SYN107 Optimizations Design Cycle Drag Coefficient , CD

Case 4.2a Opt 0.0204 0.0206 0.0208 0.0210 0.0212 0.0214 0.0216 10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.50 , Ren = 5 million

ADODG-CRM CASE 4.2b DRAG HISTORY SYN107 Optimizations Design Cycle Drag Coefficient , CD

Case 4.2b Opt 0.0230 0.0232 0.0234 0.0236 0.0238 0.0240 0.0242 0.0244 0.0246 10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.55 , Ren = 5 million

ADODG-CRM CASE 4.2c DRAG HISTORY SYN107 Optimizations Design Cycle Drag Coefficient , CD

Case 4.2c Opt

0.162
0.163
0.164
0.165
0.166
0.167
0.168
0.169
0.170
0.171
0.172
0.173

10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.45 , Ren = 5 million

ADODG-CRM CASE 4.2a PITCHING-MOMENT HISTORY SYN107 Optimizations Design Cycle Pitching-Moment Coefficient , CMP

Case 4.2a Opt

0.178
0.180
0.182
0.184
0.186
0.188
0.190

10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.50 , Ren = 5 million

ADODG-CRM CASE 4.2b PITCHING-MOMENT HISTORY SYN107 Optimizations Design Cycle Pitching-Moment Coefficient , CMP

Case 4.2b Opt

0.194
0.196
0.198
0.200
0.202
0.204
0.206

10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.55 , Ren = 5 million

ADODG-CRM CASE 4.2c PITCHING-MOMENT HISTORY SYN107 Optimizations Design Cycle Pitching-Moment Coefficient , CMP

Case 4.2c Opt

ADO-DG Case 4.2 SYN107 Design-Cycle Histories.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 40

SLIDE 40

SYMBOL SOURCE

Baseline Case 4.2 Opt

ALPHA

1.816 2.146

CL

0.4497 0.4489

CD

0.01905 0.01856

CM

0.16701
0.16295

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION

REN = 5.00 , MACH = 0.850

John C. Vassberg 18:03 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 41

SLIDE 41

10 20 30 40 50 60 70 80 90 100 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 SPANLOAD & SECT CL PERCENT SEMISPAN

C*CL/CREF CL

SYMBOL SOURCE

Baseline Case 4.2 Opt

ALPHA

1.816 2.146

CL

0.4497 0.4489

CD

0.01905 0.01856

CM

0.16701
0.16295

COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION

REN = 5.00 , MACH = 0.850

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 42

SLIDE 42

SYMBOL SOURCE

Baseline Case 4.2 Opt

ALPHA

2.196 2.522

CL

0.5011 0.4989

CD

0.02155 0.02059

CM

0.18517
0.17821

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION

REN = 5.00 , MACH = 0.850

John C. Vassberg 18:08 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 43

SLIDE 43

0.0 10.0 20.0 30.0 40.0 50.0 60.0 70.0 80.0 90.0 100.0 110.0 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 SPANLOAD & SECT CL PERCENT SEMISPAN

C*CL/CREF CL

SYMBOL SOURCE

Baseline Case 4.2 Opt

ALPHA

2.196 2.522

CL

0.5011 0.4989

CD

0.02155 0.02059

CM

0.18517
0.17821

COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION

REN = 5.00 , MACH = 0.850

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 44

SLIDE 44

SYMBOL SOURCE

Baseline Case 4.2 Opt

ALPHA

2.552 2.868

CL

0.5513 0.5489

CD

0.02453 0.02311

CM

0.20390
0.19507

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION

REN = 5.00 , MACH = 0.850

John C. Vassberg 18:11 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 45

SLIDE 45

10 20 30 40 50 60 70 80 90 100 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 SPANLOAD & SECT CL PERCENT SEMISPAN

C*CL/CREF CL

SYMBOL SOURCE

Baseline Case 4.2 Opt

ALPHA

2.552 2.868

CL

0.5513 0.5489

CD

0.02453 0.02311

CM

0.20390
0.19507

COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION

REN = 5.00 , MACH = 0.850

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 46

SLIDE 46

SYMBOL SOURCE

Case 4.2a Case 4.2b Case 4.2c

ALPHA

2.146 2.522 2.868

CL

0.4489 0.4989 0.5489

CD

0.01856 0.02059 0.02311

CM

0.16295
0.17821
0.19507

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION

REN = 5.00 , MACH = 0.850

John C. Vassberg 17:41 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 47

SLIDE 47

ADO-DG CASE 4.3: Triple-Point M

M = [0.84 , 0.85 , 0.86], CL = 0.50, Re = 5.0×106
Design Cycle Histories, All 3 Conditions

– Drag & Pitching Moment

Baseline .vs. Final Design Comparisons

– Overlaid Pressure Distributions – Overlaid Spanload Distributions

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 48

SLIDE 48

0.02045 0.02050 0.02055 0.02060 0.02065 0.02070 0.02075 0.02080 0.02085 0.02090 0.02095 0.02100 10 20 30 40 50 60 70 80 90 100

Mach = 0.84 , CL = 0.50 , Ren = 5 million

ADODG-CRM CASE 4.3a DRAG HISTORY SYN107 Optimizations Design Cycle Drag Coefficient , CD

Case 4.3a Opt 0.0205 0.0206 0.0207 0.0208 0.0209 0.0210 0.0211 0.0212 0.0213 0.0214 0.0215 0.0216 10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.50 , Ren = 5 million

ADODG-CRM CASE 4.3b DRAG HISTORY SYN107 Optimizations Design Cycle Drag Coefficient , CD

Case 4.3b Opt 0.0208 0.0210 0.0212 0.0214 0.0216 0.0218 0.0220 0.0222 0.0224 0.0226 10 20 30 40 50 60 70 80 90 100

Mach = 0.86 , CL = 0.50 , Ren = 5 million

ADODG-CRM CASE 4.3c DRAG HISTORY SYN107 Optimizations Design Cycle Drag Coefficient , CD

Case 4.3c Opt

0.175
0.176
0.177
0.178
0.179
0.180
0.181
0.182
0.183
0.184

10 20 30 40 50 60 70 80 90 100

Mach = 0.84 , CL = 0.50 , Ren = 5 million

ADODG-CRM CASE 4.3a PITCHING-MOMENT HISTORY SYN107 Optimizations Design Cycle Pitching-Moment Coefficient , CMP

Case 4.3a Opt

0.177
0.178
0.179
0.180
0.181
0.182
0.183
0.184
0.185
0.186
0.187

10 20 30 40 50 60 70 80 90 100

Mach = 0.85 , CL = 0.50 , Ren = 5 million

ADODG-CRM CASE 4.3b PITCHING-MOMENT HISTORY SYN107 Optimizations Design Cycle Pitching-Moment Coefficient , CMP

Case 4.3b Opt

0.182
0.183
0.184
0.185
0.186
0.187
0.188
0.189
0.190
0.191
0.192

10 20 30 40 50 60 70 80 90 100

Mach = 0.86 , CL = 0.50 , Ren = 5 million

ADODG-CRM CASE 4.3c PITCHING-MOMENT HISTORY SYN107 Optimizations Design Cycle Pitching-Moment Coefficient , CMP

Case 4.3c Opt

ADO-DG Case 4.3 SYN107 Design-Cycle Histories.

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 49

SLIDE 49

SYMBOL SOURCE

Baseline Case 4.3

ALPHA

2.299 2.618

CL

0.5008 0.4990

CD

0.02096 0.02051

CM

0.18138
0.17550

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION

REN = 5.00 , MACH = 0.840

John C. Vassberg 18:17 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 50

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10 20 30 40 50 60 70 80 90 100 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 SPANLOAD & SECT CL PERCENT SEMISPAN

C*CL/CREF CL

SYMBOL SOURCE

Baseline Case 4.3

ALPHA

2.299 2.618

CL

0.5008 0.4990

CD

0.02096 0.02051

CM

0.18138
0.17550

COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION

REN = 5.00 , MACH = 0.840

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 51

SLIDE 51

SYMBOL SOURCE

Baseline Case 4.3 Opt

ALPHA

2.196 2.517

CL

0.5011 0.4989

CD

0.02155 0.02062

CM

0.18517
0.17768

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION

REN = 5.00 , MACH = 0.850

John C. Vassberg 18:20 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 52

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10 20 30 40 50 60 70 80 90 100 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 SPANLOAD & SECT CL PERCENT SEMISPAN

C*CL/CREF CL

SYMBOL SOURCE

Baseline Case 4.3 Opt

ALPHA

2.196 2.517

CL

0.5011 0.4989

CD

0.02155 0.02062

CM

0.18517
0.17768

COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION

REN = 5.00 , MACH = 0.850

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SLIDE 53

SYMBOL SOURCE

Baseline Case 4.3 Opt

ALPHA

2.085 2.394

CL

0.5013 0.4990

CD

0.02257 0.02090

CM

0.19136
0.18256

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION

REN = 5.00 , MACH = 0.860

John C. Vassberg 18:22 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

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10 20 30 40 50 60 70 80 90 100 0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 SPANLOAD & SECT CL PERCENT SEMISPAN

C*CL/CREF CL

SYMBOL SOURCE

Baseline Case 4.3 Opt

ALPHA

2.085 2.394

CL

0.5013 0.4990

CD

0.02257 0.02090

CM

0.19136
0.18256

COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION

REN = 5.00 , MACH = 0.860

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 55

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SYMBOL SOURCE

Case 4.3 Opt Case 4.3 Opt Case 4.3 Opt

MACH

0.840 0.850 0.860

ALPHA

2.618 2.517 2.394

CL

0.4990 0.4989 0.4990

CD

0.02051 0.02062 0.02090

CM

0.17550
0.17768
0.18256

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION

REN = 5.00

John C. Vassberg 18:25 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

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ADO-DG CASE 4 RESULTS

M = 0.85, CL = 0.50, Re = 5.0 × 106
Comparison of Baseline & Final Designs

– Tabulated Data – Overlaid Pressure Distributions

Drag Polars; Alpha Sweeps
Drag Rises; Mach Sweeps

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ADO-DG CASE 4 RESULTS

Baseline ADO-CRM-Wing. M CL CDcor CMcor 0.84 0.50 0.02092

0.18114

0.85 0.45 0.01906

0.16710

0.85 0.50 0.02149

0.18482

0.85 0.55 0.02443

0.20340

0.86 0.50 0.02249

0.19087

Case 4.1 Optimum Wing. M CL CDcor ∆CD CMcor 0.85 0.50 0.02062

0.00087
0.16750

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ADO-DG CASE 4 RESULTS

Case 4.2 Optimum Wing. M CL CDcor ∆CD CMcor 0.85 0.45 0.01861

0.00045
0.16330

0.85 0.50 0.02064

0.00085
0.17855

0.85 0.55 0.02318

0.00125
0.19548

Case 4.3 Optimum Wing. M CL CDcor ∆CD CMcor 0.84 0.50 0.02056

0.00036
0.17578

0.85 0.50 0.02066

0.00083
0.17801

0.86 0.50 0.02096

0.00153
0.18294

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SYMBOL SOURCE

Baseline Case 4.1 Opt Case 4.2 Opt Case 4.3 Opt

ALPHA

2.196 2.729 2.522 2.517

CL

0.5011 0.4983 0.4989 0.4989

CD

0.02155 0.02055 0.02059 0.02062

CM

0.18517
0.16695
0.17821
0.17768

COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4 OPTIMIZATIONS

REN = 5.00 , MACH = 0.850

John C. Vassberg 17:15 Sun 14 Dec 14 COMPPLOT Ver 2.04

Solution 1 Upper-Surface Isobars

( Contours at 0.05 Cp )

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

6.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

18.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

31.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

43.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

56.2% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

68.8% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

81.3% Span

0.2 0.4 0.6 0.8 1.0

1.5
1.0
0.5

0.0 0.5 Cp X / C

93.8% Span

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0.30 0.35 0.40 0.45 0.50 0.55 0.60 0.65 0.010 0.011 0.012 0.013 0.014 0.015 0.016

Mach = 0.85 , Ren = 5 million

ADODG-CRM DRAG POLARS SYN107 Optimizations Idealized Profile Drag , CD - CL^2/(Pi*AR) Lift Coefficient , CL

Baseline Case 4.1 Opt Case 4.2 Opt Case 4.3 Opt

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190 200 210 220 230 240 250 260 270 280 0.80 0.81 0.82 0.83 0.84 0.85 0.86 0.87 0.88 0.89 0.90

CL = 0.5 , Ren = 5 million

ADODG-CRM DRAG RISES SYN107 Optimizations Mach Number Drag Coefficient , CD ( counts )

Baseline Case 4.1 Opt Case 4.2 Opt Case 4.3 Opt

Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January 2015 62

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ADO-DG CASE 4 SUMMARY

Optimizations Yield Designs with

Near Theoretical Minimum Drag

– Essentially No Shock Drag – Near Minimum Induced Drag – Near Minimum Profile Drag per Thickness Distribution

Case 4.1 Single-Point Design

– Exhibits Poor Off-Design Performance

Case 4.2-4.3 Triple-Point Designs

– Relinquished < 0.5 counts at Cruise Condition

Multi-Point Optimizations Clearly

Improve Off-Design Characteristics

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SLIDE 63

Select ADO-DG Case Studies in Aerodynamic Design Optimization Antony Jameson

T. V. Jones Professor of Engineering
Dept. Aeronautics & Astronautics