No abstract

The MISSILE 3 engineering prediction method for missile acradynamic performance calculations has been improved to better predict missile longitudinal a n d lateral-directional forces a n d m o m e n t s a s well as individual fin forces a n d m o m e n t s . T h e m e t h o d considers nonlinear effects such as induced rolling moments due to the influence of asymmetric canard and body vorticity on missile tail fins. In addition, c o n r p a r i s o n s w i t h e x p e r i m e n t a t t r a n s o n i c (0.8 5 Mm 5 1.2) and high Mach numbers (Mm > 4 ) and high angles of attack ( a 5 45') indicate that this prediction method is applicable t o e x t r e m e flight conditions. Recent modifications to the MISSILE 3 code are described, and a number of measured and predicted aerodynamic characteristics are provided t o demonstrate the capabilitics and limitations of this last& version.

No abstract

No abstract

No abstract