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Hands-On Example Cases

Hands-On Example Cases. 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

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Hands-On Example Cases

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  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/raetaf.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/m6wing.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/nlrflap.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/axinoz.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/hypramp.html

  9. 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 Plot3d solution file http://www.grc.nasa.gov/www/wind/valid/stube/stube.html

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