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Flows over wings with leading-edge vortex separation
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rao, B. M. Maskew, B. |
| Copyright Year | 1982 |
| Description | The unsteady cross flow analogy reduces the steady three dimensional separation flow problem into an unsteady two dimensional flow problem in which the section shape changes with time. The two dimensional VORSEP code is extended to the case of arbitrary body growth rates in order to generate the initial vortex structures for the three dimensional free vortex sheet (FVS) code. Automatic procedures to reduce the wing geometry definition to a set of cross flow plane sections corresponding to the locations of the time step solutions and to generate the effective source distribution on each cross flow section to represent the section normal growth across the following steps are incorporated in the VORSEP code. Also, the wake shedding model is improved by adopting a redistribution scheme which improves the stability of the free sheet development with time. The improved wake shedding model combined with the redistribution scheme alleviated the numerical instabilities associated with the vortex rollup. |
| File Size | 724803 |
| Page Count | 46 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820018362 |
| Archival Resource Key | ark:/13960/t23c0vz99 |
| Language | English |
| Publisher Date | 1982-04-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Vortex Sheets Vortex Shedding Time Functions Wing Profiles Flow Geometry Two Dimensional Flow Separated Flow Leading Edges Computer Programs Cross Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
