Case 2 DPW-W1/W2 Drag Prediction for the 3 CFD …Case 2 DPW-W1/W2 Drag Prediction for the 3rd CFD...

Tinoco & Venkatakrishnan

3rd CFD Drag Prediction WorkshopSan Francisco, California – June 2006

Case 2 DPW-W1/W2 Drag Prediction for the3rd CFD Drag Prediction Workshop

Edward N. Tinoco&

Venkat Venkatakrishnan

Enabling Technology & ResearchBoeing Commercial Airplanes

P.O. Box 3707 MC 67-LKSeattle, WA 98124-2207

Investigate the use of a “Production Navier-Stokes AnalysisSystem” for CFD Drag Prediction

-Major interest is in the prediction of drag increments

-Use “standard” processes as much as possibleAcknowledgement

None of this work would have been possible without the considerable contributions of:N. Jong Yu

Tsu-Yi Bernard SuTsong-Jhy Kao

Senthan SwaminathanMoeljo Hong

Emanuel R Setiawan

Objective

• Developed at NASA Langley (Jim Thomas, Kyle Anderson, BobBiedron, Chris Rumsey, & …)

• Finite volume• Upwind biased and central difference• Multigrid and mesh sequencing for acceleration• Multiblock with 1-1 blocking, patched grid, and overlap-grid• Numerous turbulence models

– Spalart-Almaras SA Model– Menter’s k-ω SST Model

• Time accurate with dual-time stepping• Runs efficiently on parallel machines through MPI

Run with ICEM Generated Structured Grids

CFL3D – Thin Layer Navier-Stokes Code

• Developed by Metacomp Technogies• Unified grid, unified physics and advanced numerical discretization and

solution framework.• Finite volume• Upwind biased• Multigrid for acceleration• Arbitrary elements and has overset capabilities.• Choice of turbulence models

– Spalart-Almaras SA Model– k-ε-Rt Μodel

• Time accurate with dual-time stepping• Runs efficiently on parallel machines through MPI

Limited runs with:– ICEM Structured Grids– Cessna Unstructured Grids

CFD++ – Unstructured Grid Navier-Stokes Code

DPW-W2 Creation

Objective: Create a companion wing to DPW-W1 for drag increment prediction• Maintain the same planform and thickness• Use optimization to change camber and twist

• TRANAIR single-point optimization– Sequential Quadratic Programming

– Linear Constraints– Nonlinear Objectives

• Minimize drag at a specified lift• Variables: 5 camber variables + twist + shear @ 7 spanwise locations

DPW-W1 DPW-W2

DPW-W1/W2 Shape Comparisons

DPW-W1/W2 ICEM Structured GridsMedium Grid

DPW-W1/W2Typical K-GridO-O Topology

DPW-W1/W2Typical I-GridO Topology

Structured Multi-Block DPW-W1/W2 GridsConstructed with ICEM

Gridding Guidelines not met - Grids were not uniformly refined!

I_1 I-2 I_3 J_1 J_2 J_3 K_1 K_2 Total Grid Size

Coarse 73 25 73 49 25 49 33 49 1.60E+06

Medium 81 33 81 73 33 73 49 73 4.20E+06

Medium Fine 121 49 121 73 49 73 65 97 8.60E+06

Fine 145 49 145 105 49 105 73 105 1.47E+07

J_2K_1

DPW-W1/W2 – Drag Convergence – CFL3D

DPW-W1 – Wing Cp’s – Grid Convergence – CFL3D

DPW-W1 – Wing Cp’s – Turbulence Modeling Effects – CFL3D

DPW-W1 vs W2 – Wing Cp’s – CFL3D

DPW-W1 / W2 – Lift and Pitching Moment – CFL3D

DPW-W1 / W2 – Polar Shape - Code/Turbulence Modeling

DPW-W1 / W2 – Drag Polar Increments

DPW-W1 / W2 – Total Drag Grid Convergence – CFL3D

DPW-W1 / W2 – Skin Friction Grid Convergence – CFL3D

DPW-W1 / W2 – Drag Increment Grid Convergence – CFL3D

DPW-W1 / W2 – Total Drag Grid Convergence – CFD++

DPW-W1 / W2 – Drag Increment Grid Convergence – CFD++

Concluding RemarksCFL3D – Structured ICEM Grids

•Convergence characteristics not as good as seen for F6 cases

•More variation in grids

CFD++ - Structured ICEM Grids

• Good convergence characteristics

CFD++ - Unstructured Cessna Grids

• No convergence problems on Cessna medium grid for W1.

• Divergence observed on all cases for W2 except for a =2 deg.Solution for all other angles obtained using this as a restart solution.

We should rename to the Grid Convergence Workshop

Backup

DPW-W1 Pressure Distributions

DPW-W2 Pressure Distributions

Case 2 DPW-W1/W2 Drag Prediction for the 3 CFD …Case 2 DPW-W1/W2 Drag Prediction for the 3rd CFD...

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