A method for predicting the detailed pressure distribution on wing-body combinations at transonic speeds is described. The basic inviscid method is the modified transonic small disturbance theory program developed by Ballhaus, Bailey and Frick. In order to provide accurate surface pressure predictions on the wing, several additional features of typical transonic flowfields have been incorporated. These consist of the viscous displacement effect, local strong viscous interaction at the shock wave foot and at the trailing edge (including an approximate treatment of local shallow separations) and the interaction effect of the fuselage. In addition, the code has been designed to provide the user with an extremely easy to use and reliable engineering tool. (DePo)
A numerical three-dimensional viscous transonic wing-body analysis and design tool
Numerische dreidimensionale Analyse und Entwurfshilfe fuer Tragfluegelkonstruktion fuer zaehe, transsonische Stroemungen
AIAA-Papers ; 1-16
1978
16 Seiten, 11 Bilder, 42 Quellen
Conference paper
English