Some Aerodynamic Performance Calculations on Missile Configurations.
Final rept. 15 Jan 77-30 Nov 78,
TENNESSEE UNIV SPACE INST TULLAHOMA
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Axisymmetric bodies with a clean configuration have a rather flat pressure distribution on the cylindrical portion of the body. In this report, axisymmetric bodies with surface cut outs are modelled using an inviscid flow approach with experimental flow results. Literature is available on numerical schemes for aerodynamic calculations on fins at moderately high angles of attack. Fin-body combinations are studied using a nose vortex model and some results reported. Also studied is the asymmetric nose vortex problem on an axisymmetric body at higher angles of attack. This has been studied for conical and ogive forebodies using a modified Wardlows method. Author
- Guided Missiles
- Fluid Mechanics