Loading...
Please wait, while we are loading the content...
Similar Documents
Two and three-dimensional shock-shock interactions on the blunt leading edges of the hypersonic inlets
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Singh, D. J. Tiwari, S. N. Kumar, Ajay |
| Copyright Year | 1991 |
| Description | The effect of shock impingement on the blunt leading edges of the top and sidewall compression type inlet of a scramjet engine is studied numerically. The impinging shock is caused by the vehicle forebody. The interaction of this forebody shock with the inlet leading edge shock results in a very complex flowfield containing local regions of high pressure and intense heating. This complex flowfield in calculated by solving the Navier-Stokes equations using a finite volume flux splitting technique due to van Leer. To resolve the finer details of the flow structure as well as to predict the surface heat transfer accurately, adaptive grid technique is used in the analysis. Results of the present numerical study are compared with available experimental results. |
| File Size | 1293105 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910011775 |
| Archival Resource Key | ark:/13960/t9h46n67h |
| Language | English |
| Publisher Date | 1991-01-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Computational Fluid Dynamics Interactional Aerodynamics Supersonic Combustion Ramjet Engines Finite Volume Method Hypersonic Inlets High Pressure Navier-stokes Equation Shock Waves Impingement Flow Distribution Computational Grids Blunt Leading Edges Forebodies Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
