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Distribution of wave drag and lift in the vicinity of wing tips at supersonic speeds
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1947 |
| Description | The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at supersonic speeds was extended to include the effect of the region between the wing boundary and the foremost Mach wave from the wing leading edge. The effect of this region on the surface velocity potential has been determined by an equivalent function, which is evaluated over a portion of the wing surface. In this manner, the effect of angles of attack and yaw as well as the asymmetry of top and bottom wing surfaces may be calculated. As examples of the method, the pressure distribution on a thin plate wing of rectangular plan form as well as the lift and the drag coefficients as a function of Mach number, angle of attack, and aspect ratio are calculated. The equations for the surface velocity potential of several other plan forms are also included. (author) |
| File Size | 1081602 |
| Page Count | 35 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930082018 |
| Archival Resource Key | ark:/13960/t9672sg1k |
| Language | English |
| Publisher Date | 1947-01-01 |
| Access Restriction | Open |
| Subject Keyword | Airfoils, Flat-plate Wings, Sweptback Theories - Flow - Supersonic Theories - Airfoils - Thin Airfoils, Wedge Lift Distribution - Wing Tips Theories - Flow - Linear Wings, Rectangular Drag, Wave Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
