Preliminary calculations of delta wings in supersonic flow were made with a method based on theoretical work of Oswatitsch and Sun. The flow field is computed with acoustic theory for an image wing in the characteristic space. Following that, the real wing's coordinates in physical space are calculated. The planform of the image wing must be modified until the corresponding real wing has obtained the wanted shape. The theory is of first order accuracy expressed in the characteristic variables. Traces of the characteristics in physical space and bow shock waves were found for cases with wings with and without incidence. As the wing disturbances increase it becomes more difficult to give to the real wing the wanted shape. The possible practical use of the method is probably limited to slender wings at small incidences.
Calculations by a First Order Theory of Supersonic Flow around delta Wings
1980
22 pages
Report
No indication
English
Nonlinear Supersonic Potential Flow over Delta Wings
AIAA | 1981
|Delta wings for supersonic transport
Engineering Index Backfile | 1963
|Supersonic aerodynamics of delta wings
NTRS | 1988
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