HandsOn Example Cases 1 HandsOn Example Cases The

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Hands-On Example Cases 1

Hands-On Example Cases 1

Hands-On Example Cases The following example cases demonstrate step-by-step the procedures for using the

Hands-On Example Cases The following example cases demonstrate step-by-step the procedures for using the NPARC Flow Simulation System: RAE 2822 Transonic Airfoil ONERA M 6 Transonic Wing NLR Airfoil with Flap S-Duct Supersonic Axisymmetric Jet Flow Hypersonic Ramp Shock Tube Other example cases are available in the NPARC Alliance Verification and Validation Archive (www. grc. nasa. gov/www/wind/valid) 2

RAE 2822 Transonic Airfoil • • • Mach = 0. 729 2. 31 degrees

RAE 2822 Transonic Airfoil • • • Mach = 0. 729 2. 31 degrees AOA One-zone 369 x 65 C-grid Full Navier-Stokes equations Turbulent flow (Spalart-Allmaras) http: //www. grc. nasa. gov/www/wind/valid/raetaf. html 3

ONERA M 6 Wing • • Mach = 0. 84 3. 06 degrees AOA

ONERA M 6 Wing • • Mach = 0. 84 3. 06 degrees AOA Four-zone H-grid Full Navier-Stokes equations Turbulent flow (Spalart-Allmaras) Wall function Parallel processing Integrated flow quantities during solution (lift, drag) • Post-processing (z-cuts for Cp, integration of forces on wing) http: //www. grc. nasa. gov/www/wind/valid/m 6 wing. html 4

NLR Airfoil with Flap • • Mach = 0. 2 Turbulent flow (Spalart-Allmaras) 0.

NLR Airfoil with Flap • • Mach = 0. 2 Turbulent flow (Spalart-Allmaras) 0. 0 degrees AOA 2 zone overlapped (Chimera) C-grids http: //www. grc. nasa. gov/www/wind/valid/nlrflap. html 5

Subsonic S-Duct • • • Mach = 0. 21 0. 0 degrees AOA 3

Subsonic S-Duct • • • Mach = 0. 21 0. 0 degrees AOA 3 D, internal flow Inviscid flow Singular axis 2 contiguous abutting zones Auto-couple of abutting zones Outflow BC Constant-pressure outflow Mass-flux convergence monitoring http: //www. grc. nasa. gov/www/wind/valid/sduct. html 6

Supersonic Axisymmetric Jet • • • Axisymmetric flow Arbitrary inflow with Pt and Tt

Supersonic Axisymmetric Jet • • • Axisymmetric flow Arbitrary inflow with Pt and Tt specified Flow initialization from arbitrary inflow Turbulent flow (Spalart-Allmaras) Multi-zone (3 zones with H-grids) Parallel processing http: //www. grc. nasa. gov/www/wind/valid/axinoz. html 7

Hypersonic Ramp • • Mach = 7. 0 Laminar flow 15 degree ramp 0.

Hypersonic Ramp • • Mach = 7. 0 Laminar flow 15 degree ramp 0. 0 degrees AOA Two-dimensional Time-dependent & PNS Various “high-temperature” / chemistry models http: //www. grc. nasa. gov/www/wind/valid/hypramp. html 8

Shock Tube • • • 10 / 1 pressure ratio (Sod’s problem) Unsteady, inviscid

Shock Tube • • • 10 / 1 pressure ratio (Sod’s problem) Unsteady, inviscid flow Time-accurate implicit and explicit methods Axisymmetric Initialize common solution file (. cfl) from Plot 3 d solution file http: //www. grc. nasa. gov/www/wind/valid/stube. html 9

INSTALLATION HANDSON About the HandsOn This handson sectionINSTALLATION HANDSON About the HandsOn This handson section
INSTALLATION HANDSON About the HandsOn This handson sectionINSTALLATION HANDSON About the HandsOn This handson section
ADMINISTRATION HANDSON About the HandsOn This handson sectionADMINISTRATION HANDSON About the HandsOn This handson section
ScoreP HandsOn CUDA Jacobi example SC 13 HandsonScoreP HandsOn CUDA Jacobi example SC 13 Handson
ROOM ACOUSTICS II EXAMPLE PROBLEM EXAMPLE EXAMPLE EXAMPLEROOM ACOUSTICS II EXAMPLE PROBLEM EXAMPLE EXAMPLE EXAMPLE
Example 1 Example 2 Example 3 Example 4Example 1 Example 2 Example 3 Example 4
DECISION TREE Example Example DECISION TREE Example ExampleDECISION TREE Example Example DECISION TREE Example Example
Deadlocks Example 1 Example 2 Example 2 ExampleDeadlocks Example 1 Example 2 Example 2 Example