1 / 9

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

romerop
Download Presentation

Hands-On Example Cases

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript


  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

More Related