A numerical procedure has been developed for the computation of the steady, inviscid supersonic flow over aircraft configurations. The technique accounts for major nonlinear effects (shock waves, blunt leading edges) at low to moderate supersonic speeds. A fully implicit marching technique for the full potential equation is utilized in a stereographically projected, conformally mapped, spherical coordinate frame. Cross-flow planes are efficiently solved by type-dependent relaxation techniques. Results are presented for several delta wing configurations and bodies of revolution, and are compared with existing experimental data, Euler's equations solutions and results from linearized theories (panel methods). (Peters)
The nonlinear supersonic potential flow over delta wings
Die nichtlineare Ueberschallpotentialstroemung ueber Deltafluegeln
AIAA-Papers ; 1-12
1980
12 Seiten
Aufsatz (Konferenz)
Englisch
Nonlinear Supersonic Potential Flow over Delta Wings
AIAA | 1981
|The nonlinear supersonic potential flow over delta wings
AIAA | 1980
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AIAA | 1984
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