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Analysis of the flow about delta wings with leading edge separation at supersonic speeds
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Nenni, J. P. Tung, C. |
| Copyright Year | 1973 |
| Description | A research program was conducted to develop an improved theoretical flow model for the flow about sharp edge delta wings with leading-edge separation at supersonic speeds. The flow model incorporates a representation of the secondary separation region which occurs just inboard of the leading edge on such wings and is based on a slender-wing theory whereby the full three-dimensional problem is reduced to a quasi two-dimensional problem in the cross-flow plane. The secondary separation region was modeled by a surface distribution of singularities or a linearized type of cavity representation. The primary vortex and separation were modeled by a concentrated vortex and cut in the cross-flow potential which represents its feeding sheet. The cross-flow solutions for the cavity model were obtained, but these solutions have physical significance only in a very restricted range of angle of attack. The reasons for the failure of the flow model are discussed. The analysis is presented so that other interested researchers may critically review the work. |
| File Size | 1468366 |
| Page Count | 42 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740006632 |
| Archival Resource Key | ark:/13960/t91882n0q |
| Language | English |
| Publisher Date | 1973-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Slender Wings Supersonic Flow Turbulent Wakes Vortices Delta Wings Flow Distribution Sharp Leading Edges Two Dimensional Flow Separated 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 |
