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Investigation of supersonic turbulent boundary-layer separation on a compression ramp by an integral method
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Patel, D. K. Czarnecki, K. R. |
| Copyright Year | 1977 |
| Description | An investigation was made to determine the feasibility of using a boundary layer integral method to study the separation of a turbulent boundary layer on a two dimensional ramp at supersonic speeds. The numerical calculations were made for a free stream Mach number of 3, a Reynolds number of 10 million, and over a ramp angle range from 0 deg to 30 deg. For ramp angles where no flow separation was indicated, theoretical calculations were in reasonable agreement with experimental data except for a somewhat belated rise in pressure. For larger ramp angles, where separation was present, the investigation produced results that were not in agreement with experiment or with results calculated by time dependent Navier-Stokes methods. This apparently was true because no provision had been made for a proper shock boundary layer interaction where strong normal pressure gradients are induced within the boundary layer under the shock independent of surface curvature effects. |
| File Size | 1714658 |
| Page Count | 62 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770026495 |
| Archival Resource Key | ark:/13960/t4jm72d6t |
| Language | English |
| Publisher Date | 1977-10-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Navier-stokes Equation Boundary Layer Separation Turbulent Boundary Layer Integral Calculus Supersonic Speed Pressure Gradients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
