In the study described, a finite difference approach to solving the rotational Euler equations, explicitly fitting shocks as a boundary, is applied to a variety of geometrical shapes in the lower supersonic Mach number regime. It is shown how special techniques based onthe physics of the flow can used to circumvent a variety of numerical difficulties encountered with the conical flow problem that are primarily associated with the initial value characteristics of the hyperbolic scheme, causing embedded shock-induced entropy and crossflow layers to develop on the body surface. (Jensen)
Investigation of crossflow shocks on delta wings in supersonic flow
Untersuchungen ueber stossartige Profilumstroemungen an Deltafluegeln bei Ueberschallstroemung
AIAA Journal ; 18 , 1 ; 85-93
1980
9 Seiten, 17 Bilder, 17 Quellen
Article (Journal)
English
Nonlinear Supersonic Potential Flow over Delta Wings
AIAA | 1981
|Delta wings for supersonic transport
Engineering Index Backfile | 1963
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