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Numerical simulation of supersonic compression corners and hypersonic inlet flows using the rplus2d code
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kapoor, Kamlesh Anderson, Bernhard H. Shaw, Robert J. |
| Copyright Year | 1994 |
| Description | A two-dimensional computational code, PRLUS2D, which was developed for the reactive propulsive flows of ramjets and scramjets, was validated for two-dimensional shock-wave/turbulent-boundary-layer interactions. The problem of compression corners at supersonic speeds was solved using the RPLUS2D code. To validate the RPLUS2D code for hypersonic speeds, it was applied to a realistic hypersonic inlet geometry. Both the Baldwin-Lomax and the Chien two-equation turbulence models were used. Computational results showed that the RPLUS2D code compared very well with experimentally obtained data for supersonic compression corner flows, except in the case of large separated flows resulting from the interactions between the shock wave and turbulent boundary layer. The computational results compared well with the experiment results in a hypersonic NASA P8 inlet case, with the Chien two-equation turbulence model performing better than the Baldwin-Lomax model. |
| File Size | 6184667 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19950009623 |
| Archival Resource Key | ark:/13960/t0wq4wp48 |
| Language | English |
| Publisher Date | 1994-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Ramjet Engines Computational Fluid Dynamics Supersonic Combustion Ramjet Engines Corner Flow Turbulent Boundary Layer Shock Wave Interaction Inlet Flow Two Dimensional Flow Hypersonic Inlets Computer Programs Hypersonic Speed Supersonic Speed Turbulence Models Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
