HandsOn Example Cases

1
Hands-On Example Cases
2
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 M6 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)

3
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/raet
af.html
4
ONERA M6 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/m6wing/m6wi
ng.html
5
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/nlr
flap.html
6
Subsonic S-Duct

• Mach 0.21
• 0.0 degrees AOA
• 3D, 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/sduct
.html
7
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/axin
oz.html
8
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/hyp
ramp.html
9
Shock Tube

• 10 / 1 pressure ratio (Sods problem)
• Unsteady, inviscid flow
• Time-accurate implicit and explicit methods
• Axisymmetric
• Initialize common solution file (.cfl) from
  Plot3d solution file

http//www.grc.nasa.gov/www/wind/valid/stube/stube
.html