Within slender body theory, vortex method is developed for study of aerodynamic interference between missile, in both captive and dropped positions, and carrying airplane; in crossflow plane, airplane fuselage is approximated by circle represented by doublet; airplane wing, pylons, and missile wing panels are represented by evenly distributed vortices; case of cruciform missile carried underneath vertical pylon or dropped therefrom on each side of airplane is considered; normal force, side force, and rolling moment on missile are computed; they agree with results obtained by electric analogy; ways of improving method in light of results obtained by latter, wind tunnel, and flight test of actual configurations are indicated. (12171)
Vortex method for study of airplane-missile aerodynamic interference
J Aircraft
Journal of Aircraft ; 5 , n 6 ; p 591-597
1968
7 pages
Aufsatz (Zeitschrift)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
Aerodynamic study of airplane models
Engineering Index Backfile | 1946
|Application of Favorable Aerodynamic Interference to Supersonic Airplane Design
SAE Technical Papers | 1990
|Computational Fluid Dynamics Modeling of Multibody Missile Aerodynamic Interference
British Library Conference Proceedings | 1998
|Airplane propeller interference study
Engineering Index Backfile | 1926
|