A new method for the design of shock-free supercritical airfoils, wings, and three-dimensional configurations is described. Results illustrating this procedure in two and three dimensions are given. They include modifications to part of the upper surface of an NACA 64A410 airfoil that will maintain shock-free flow over a range of Mach numbers for a fixed lift coefficient, and the modifications required on part of the upper surface of a swept wing with an NACA 64A410 root section to achieve shock-free flow. While the results are given for inviscid flow, the same procedure can be employed iteratively with a boundary-layer calculation in order to achieve shock-free viscous designs. With a shock-free pressure field, the boundary-layer calculation will be reliable and not complicated by the difficulties of shock wave, boundary-layer interaction. (Jensen)
New method for designing shock-free transonic configurations
Eine neue Methode zum Entwurf von Bauteilen fuer schallnahe Geschwindigkeit mit stossfreiem Stroemungsverlauf
AIAA Journal ; 17 , 7 ; 722-729
1979
8 Seiten, 12 Bilder, 23 Quellen
Aufsatz (Zeitschrift)
Englisch
Transonic Aircraft Configurations
AIAA | 2012
|Transonic flow about lifting configurations.
NTRS | 1973
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