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Calculation of supersonic viscous flow over delta wings with sharp subsonic leading edges
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Tannehill, J. C. Vigneron, Y. C. Rakich, J. V. |
| Copyright Year | 1978 |
| Description | Two complementary procedures were developed to calculate the viscous supersonic flow over conical shapes at large angles of attack, with application to cones and delta wings. In the first approach the flow is assumed to be conical and the governing equations are solved at a given Reynolds number with a time-marching explicit finite-difference algorithm. In the second method the parabolized Navier-Stokes equations are solved with a space-marching implicit noniterative finite-difference algorithm. This latter approach is not restricted to conical shapes and provides a large improvement in computational efficiency over published methods. Results from the two procedures agree very well with each other and with available experimental data. |
| File Size | 1961258 |
| Page Count | 81 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780018158 |
| Archival Resource Key | ark:/13960/t1ck36g64 |
| Language | English |
| Publisher Date | 1978-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Supersonic Flow Navier-stokes Equation Algorithms Delta Wings Conical Bodies Finite Difference Theory Sharp Leading Edges Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
