Abstract:
Studying the flow over bodies of revolution is crucial to the design of missiles and
obtaining the correct shape which has a large impact on the performance of the missile.
Three-dimensional flow simulation over a body of revolution were carried out in order
to obtain flow field parameters for different angles of attack namely -4.09, -2.04, 2.06,
4.11, 6.17 and 12.41˚ at Mach number of 0.5 (subsonic) and of -4.34, -2.15, 2.17, 4.37,
8.87, and 13.6˚ at Mach number of 1.2 ( transonic flow conditions). The software
FLUENT with its prepressor GAMBIT were used to model a missile of known
geometry. The Computational Fluid dynamics results were validated with a prepublished
experimental data measured by a wind tunnel [1]
The validated model was used to examine Magnus effect on the spinning missile
which improves the effect of the high spinning rate on the side force affecting the
missile body.