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Effects of nose bluntness and shock-shock interactions on blunt bodies in viscous hypersonic flows
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Singh, D. J. Tiwari, S. N. |
| Copyright Year | 1990 |
| Description | A numerical study was conducted to investigate the effects of blunt leading edges on the viscous flow field around a hypersonic vehicle such as the proposed National Aero-Space Plane. Attention is focused on two specific regions of the flow field. In the first region, effects of nose bluntness on the forebody flow field are investigated. The second region of the flow considered is around the leading edges of the scramjet inlet. In this region, the interaction of the forebody shock with the shock produced by the blunt leading edges of the inlet compression surfaces is analyzed. Analysis of these flow regions is required to accurately predict the overall flow field as well as to get necessary information on localized zones of high pressure and intense heating. The results for the forebody flow field are discussed first, followed by the results for the shock interaction in the inlet leading edge region. |
| File Size | 4534359 |
| Page Count | 187 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19900011634 |
| Archival Resource Key | ark:/13960/t90915m97 |
| Language | English |
| Publisher Date | 1990-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Noses Forebodies Heating Supersonic Combustion Ramjet Engines Flow Distribution National Aerospace Plane Program Hypersonic Flow Regions Blunt Leading Edges Forebodies Viscous Flow High Pressure Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
