# Presentation: 714590

- 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)

- 	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)

- Hands-On Example Cases

## Mach = 0.729
2.31 degrees AOA
One-zone 369 x 65 C-grid
Full Navier-Stokes equations
Turbulent flow (Spalart-Allmaras)

- 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/raetaf.html

- RAE 2822 Transonic Airfoil

## 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)

- 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/m6wing.html

- ONERA M6 Wing

## Mach = 0.2
Turbulent flow (Spalart-Allmaras)
0.0 degrees AOA
2 zone overlapped (Chimera) C-grids

- Turbulent flow (Spalart-Allmaras)
- 0.0 degrees AOA
- 2 zone overlapped (Chimera) C-grids

- http://www.grc.nasa.gov/www/wind/valid/nlrflap/nlrflap.html

- NLR Airfoil with Flap

## 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

- 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

- Subsonic S-Duct

## 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

- 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/axinoz.html

- Supersonic Axisymmetric Jet

## Mach = 7.0
Laminar flow
15 degree ramp
0.0 degrees AOA
Two-dimensional
Time-dependent & PNS
Various “high-temperature” / chemistry models

- 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/hypramp.html

- Hypersonic Ramp

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

- 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

- Shock Tube