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The design of supercritical wings by the use of three-dimensional transonic theory
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Mann, M. J. |
| Copyright Year | 1979 |
| Description | A procedure was developed for the design of transonic wings by the iterative use of three dimensional, inviscid, transonic analysis methods. The procedure was based on simple principles of supersonic flow and provided the designer with a set of guidelines for the systematic alteration of wing profile shapes to achieve some desired pressure distribution. The method was generally applicable to wing design at conditions involving a large region of supercriterical flow. To illustrate the method, it was applied to the design of a wing for a supercritical maneuvering fighter that operates at high lift and transonic Mach number. The wing profiles were altered to produce a large region of supercritical flow which was terminated by a weak shock wave. The spanwise variation of drag of this wing and some principles for selecting the streamwise pressure distribution are also discussed. |
| File Size | 1172710 |
| Page Count | 33 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790008633 |
| Archival Resource Key | ark:/13960/t9f52gb7f |
| Language | English |
| Publisher Date | 1979-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Pressure Distribution Supercritical Wings Transonic Flow Maneuverability Three Dimensional Flow Fighter Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
