Select ADO-DG Case Studies in Aerodynamic Design Optimization
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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 , 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
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 SYN107 Optimizations Case Summary Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
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 y A (x) = ± ( x x x x x 4) Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
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 , July-August, 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
5 BASELINE NACA0012-ADO SOLUTION NACA0012-ADO - JCV AR=1 GRID MACH ALPHA CL CD CM GRID 2048x 2048 NCYC 500 RED CP MACH: MIN MAX CONTOURS 50 FLO82 Solution for NACA0012-ADO Airfoil at M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
6 SYN83 OPTIMIZATION SYN83 C-mesh (768x128) about NACA0012-ADO. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
7 SYN83 OPTIMIZATION SYN83 Results (C d in counts). Airfoil C d C d Seed NACA0012-ADO Design SYNA Seed SEEDB Design SYNB Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
8 SYN83 OPTIMIZATION NADOV01 OPTIMUM AIRFOIL MACH ALPHA CL CD CM GRID 2048x 2048 NCYC 500 CP MACH: MIN MAX CONTOURS 60 FLO82 Solution for SYNA Airfoil at M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
9 SYN83 OPTIMIZATION NADOV02 OPTIMUM AIRFOIL MACH ALPHA CL CD CM GRID 2048x 2048 NCYC 500 CP MACH: MIN MAX CONTOURS 60 FLO82 Solution for SYNB Airfoil at M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
10 FLO82 O-MESH Close-up view of the NACA0012-ADO 256x256 O-mesh. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
11 (256 x 256) (512 x 512) S S S S Log(Error) -8.0 R 0.6 Nsup Log(Error) -8.0 R 0.6 Nsup D R R D L L L L D D Work FLO82 Convergence Histories at M = 0.85, α = 0. Work Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
12 (1024 x 1024) (2048 x 2048) S S S S 1.0 R Log(Error) -8.0 R 0.6 Nsup Log(Error) Nsup D R R D L L L L D D Work FLO82 Convergence Histories at M = 0.85, α = 0. Work Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
13 FLO82 CROSS-ANALYSIS FLO82 Drag Assessment (C d in counts). Airfoil N256 N512 N1024 N2048 C d NACA0012-ADO SYNA SEEDB SYNB NADOT SYNBT 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
14 CARRIER-DESTERAC AIRFOIL (G) CARRIER-DESTARAC BEZ96FP OPTIMUM AIRFOIL MACH ALPHA CL CD CM GRID 2048x 2048 NCYC 500 RED XCP YCP CP MACH: MIN MAX CONTOURS 60 FLO82 Solution, Carrier-Desterac Airfoil (G), M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
15 BISSON-NADARAJAH AIRFOIL (S) SIVAFOIL OPTIMUM AIRFOIL MACH ALPHA CL CD CM GRID 2048x 2048 NCYC 500 RED CP MACH: MIN MAX CONTOURS 70 FLO82 Solution, Bisson-Nadarajah Airfoil (S), M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
16 CARY AIRFOIL (A) ANDREW CARY OPTIMUM AIRFOIL MACH ALPHA CL CD CM GRID 2048x 2048 NCYC 500 RED CP MACH: MIN MAX CONTOURS 60 FLO82 Solution, Cary Airfoil (A), M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
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: GA: SA: GSA Triangle Interior Angles G: S: A: Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
18 A-Airfoil S-Airfoil G-Airfoil GSA Triangle & FLO82 Survey Locations. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
19 GSA FLO82 Results, M = 0.85, α = 0. G WT S WT A WT C d X TRI Y TRI A S * G Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
20 GSA FLO82 Solutions, Iso-A Contours, M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
21 GSA FLO82 Solutions, Iso-S Contours, M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
22 FLO82 Solutions, M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
23 FLO82 Solutions, Level View of Valley, M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
24 FLO82 Solutions, Elevated View of Valley, M = 0.85, α = 0. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
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
26 ADO-CRM-WING MODEL PROBLEM ADO-DG Case 4 General Statement Minimize Drag at Fixed Lifting Condition(s) Re = C M 0.17 at C L = 0 & M = 0.85 Maintain or Exceed Internal Volume of Baseline Wing Case 4.1 Single-Point M = 0.85, C L = 0 Case 4.2 Triple-Point C L Sweep M = 0.85, C L = [0.45, 0, 5], WT = [1, 2, 1] Case 4.3 Triple-Point Mach Sweep M = [0.84, 0.85, 0.86], C L = 0, WT = [1, 2, 1] Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
27 ADO-CRM-WING MODEL PROBLEM ADO-CRM-Wing Reference Quantities Sref/2 = , Cref = 1.0, b/2 = Xref = , Y ref =, Zref = SYN107 Optimizations Constrained Lifting Condition(s) Active Adjustment of α During Convergence Includes dc D /dc L Terms in Gradient Formulation Added Pitching-Moment Penalty Sufficient to Achieve C M 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
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 10 th Design Cycle 240 Iters for Analysis 160 Iters for dc D /dc L, dc M /dc L & dc L /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
29 ADO-DG CASE 4: BASELINE WING Design Pt.: M = 0.85, C L = 0, Re = Polar: C L = [0.45, 0, 5] DragRise: M = [0.84, 0.85, 0.86] Comparisons Overlaid Pressure Distributions Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
30 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Baseline Baseline ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 17:48 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
31 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION REN = SYMBOL SOURCE Baseline Baseline Baseline MACH ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 18:27 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
32 ADO-DG CASE 4.1: Single-Point M = 0.85, C L = 0, Re = 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
33 216 ADODG-CRM CASE 4.1 DRAG HISTORY SYN107 Optimizations Mach = 0.85, CL =, Ren = 5 million Case 4.1 Opt Drag Coefficient, CD Design Cycle Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
34 ADODG-CRM CASE 4.1 PITCHING-MOMENT HISTORY SYN107 Optimizations Mach = 0.85, CL =, Ren = 5 million Pitching-Moment Coefficient, CMP Case 4.1 Opt Design Cycle Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
35 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.1 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.1 Opt ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 17:34 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
36 COMPARISON OF UPPER SURFACE CONTOURS ADODG-CRM CASE 4.1 OPTIMIZATION REN = 5.00, MACH = ( Contours at 5 ) Solution 1: Baseline ALPHA = 2.20, CL = 011 CD = 2155 Solution 2: Case 4.1 Opt ALPHA = 2.73, CL = CD = 2055 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
37 COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.1 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.1 Opt ALPHA CL CD CM C*CL/CREF 0.6 SPANLOAD & SECT CL CL PERCENT SEMISPAN Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
38 ADO-DG CASE 4.2: Triple-Point C L M = 0.85, C L = [0.45, 0, 5], Re = 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
39 185 ADODG-CRM CASE 4.2a DRAG HISTORY SYN107 Optimizations Mach = 0.85, CL = 0.45, Ren = 5 million ADODG-CRM CASE 4.2b DRAG HISTORY SYN107 Optimizations Mach = 0.85, CL = 0, Ren = 5 million ADODG-CRM CASE 4.2c DRAG HISTORY SYN107 Optimizations Mach = 0.85, CL = 5, Ren = 5 million Case 4.2a Opt Case 4.2b Opt Case 4.2c Opt Drag Coefficient, CD Drag Coefficient, CD Drag Coefficient, CD Design Cycle Design Cycle Design Cycle ADODG-CRM CASE 4.2a PITCHING-MOMENT HISTORY SYN107 Optimizations Mach = 0.85, CL = 0.45, Ren = 5 million ADODG-CRM CASE 4.2b PITCHING-MOMENT HISTORY SYN107 Optimizations Mach = 0.85, CL = 0, Ren = 5 million ADODG-CRM CASE 4.2c PITCHING-MOMENT HISTORY SYN107 Optimizations Mach = 0.85, CL = 5, Ren = 5 million Pitching-Moment Coefficient, CMP Pitching-Moment Coefficient, CMP Pitching-Moment Coefficient, CMP Case 4.2a Opt Case 4.2b Opt Case 4.2c Opt Design Cycle Design Cycle Design Cycle ADO-DG Case 4.2 SYN107 Design-Cycle Histories. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
40 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.2 Opt ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 18:03 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
41 COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.2 Opt ALPHA CL CD CM C*CL/CREF SPANLOAD & SECT CL CL PERCENT SEMISPAN Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
42 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.2 Opt ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 18:08 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
43 COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.2 Opt ALPHA CL CD CM C*CL/CREF 0.6 SPANLOAD & SECT CL CL PERCENT SEMISPAN Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
44 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.2 Opt ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 18:11 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
45 COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.2 Opt ALPHA CL CD CM C*CL/CREF 0.6 SPANLOAD & SECT CL CL PERCENT SEMISPAN Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
46 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.2 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Case 4.2a Case 4.2b Case 4.2c ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 17:41 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
47 ADO-DG CASE 4.3: Triple-Point M M = [0.84, 0.85, 0.86], C L = 0, Re = 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
48 2045 ADODG-CRM CASE 4.3a DRAG HISTORY SYN107 Optimizations Mach = 0.84, CL = 0, Ren = 5 million ADODG-CRM CASE 4.3b DRAG HISTORY SYN107 Optimizations Mach = 0.85, CL = 0, Ren = 5 million ADODG-CRM CASE 4.3c DRAG HISTORY SYN107 Optimizations Mach = 0.86, CL = 0, Ren = 5 million Case 4.3a Opt 215 Case 4.3b Opt 224 Case 4.3c Opt Drag Coefficient, CD Drag Coefficient, CD Drag Coefficient, CD Design Cycle Design Cycle Design Cycle ADODG-CRM CASE 4.3a PITCHING-MOMENT HISTORY SYN107 Optimizations Mach = 0.84, CL = 0, Ren = 5 million ADODG-CRM CASE 4.3b PITCHING-MOMENT HISTORY SYN107 Optimizations Mach = 0.85, CL = 0, Ren = 5 million ADODG-CRM CASE 4.3c PITCHING-MOMENT HISTORY SYN107 Optimizations Mach = 0.86, CL = 0, Ren = 5 million Pitching-Moment Coefficient, CMP Pitching-Moment Coefficient, CMP Pitching-Moment Coefficient, CMP Case 4.3a Opt Case 4.3b Opt Case 4.3c Opt Design Cycle Design Cycle Design Cycle ADO-DG Case 4.3 SYN107 Design-Cycle Histories. Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
49 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.3 ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 18:17 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
50 COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.3 ALPHA CL CD CM C*CL/CREF 0.6 SPANLOAD & SECT CL CL PERCENT SEMISPAN Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
51 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.3 Opt ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 18:20 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
52 COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.3 Opt ALPHA CL CD CM C*CL/CREF 0.6 SPANLOAD & SECT CL CL PERCENT SEMISPAN Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
53 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.3 Opt ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 18:22 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
54 COMPARISON OF SPANLOAD DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.3 Opt ALPHA CL CD CM C*CL/CREF 0.6 SPANLOAD & SECT CL CL PERCENT SEMISPAN Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
55 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4.3 OPTIMIZATION REN = SYMBOL SOURCE Case 4.3 Opt Case 4.3 Opt Case 4.3 Opt MACH ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 18:25 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
56 ADO-DG CASE 4 RESULTS M = 0.85, C L = 0, Re = Comparison of Baseline & Final Designs Tabulated Data Overlaid Pressure Distributions Drag Polars; Alpha Sweeps Drag Rises; Mach Sweeps Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
57 ADO-DG CASE 4 RESULTS Baseline ADO-CRM-Wing. M C L C D cor C M cor Case 4.1 Optimum Wing. M C L C D cor C D C M cor Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
58 ADO-DG CASE 4 RESULTS Case 4.2 Optimum Wing. M C L C D cor C D C M cor Case 4.3 Optimum Wing. M C L C D cor C D C M cor Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
59 COMPARISON OF CHORDWISE PRESSURE DISTRIBUTIONS ADODG-CRM CASE 4 OPTIMIZATIONS REN = 5.00, MACH = SYMBOL SOURCE Baseline Case 4.1 Opt Case 4.2 Opt Case 4.3 Opt ALPHA CL CD CM % Span 93.8% Span - Solution 1 Upper-Surface Isobars ( Contours at 5 ) % Span 81.3% Span % Span 68.8% Span - - COMPPLOT Ver % Span 56.2% Span John C. Vassberg 17:15 Sun 14 Dec 14 Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
60 0.65 ADODG-CRM DRAG POLARS SYN107 Optimizations Mach = 0.85, Ren = 5 million Lift Coefficient, CL Baseline 0.35 Case 4.1 Opt Case 4.2 Opt Case 4.3 Opt Idealized Profile Drag, CD - CL^2/(Pi*AR) Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
61 280 ADODG-CRM DRAG RISES SYN107 Optimizations CL =, Ren = 5 million Baseline Case 4.1 Opt Case 4.2 Opt Case 4.3 Opt Drag Coefficient, CD ( counts ) Mach Number Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
62 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 Triple-Point Designs Relinquished < counts at Cruise Condition Multi-Point Optimizations Clearly Improve Off-Design Characteristics Jameson & Vassberg, AIAA Sci-Tech, Kissimmee FL, January
63 Select ADO-DG Case Studies in Aerodynamic Design Optimization Antony Jameson T. V. Jones Professor of Engineering Dept. Aeronautics & Astronautics Stanford University Stanford, CA , 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
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