EFFECT OF NOSE BLUNTNESS AND AFTERBODY SHAPE ON AERODYNAMIC CHARACTERISTICS OF A MONOPLANAR MISSILE CONCEPT WITH BODIES OF CIRCULAR AND ELLIPTICAL CROSS SECTIONS AT A MACH NUMBER OF 2..50

摘要

A wind-tunnel investigation has been conducted to determine the effect of nose bluntness and afterbody shape on the aerodynamic characteristics of a family of circular and modified elliptical missile configurations. These configurations were of monoplanar wing design with constant wing span. Tail surfaces were mounted flush at the body base with a dihedral angle of ±30°. The tests were performed at a Mach number of 2.50 and at angles of attack from about -4 to 32 . The results indicate that increasing nose bluntness increases zero-lift drag and decreases both the maximum lift-drag ratio and the level of directional stabil¬ity. The center of pressure generally moves forward with increasing nose size;however, small nose radii on the modified elliptical configurations move the center of pressure rearward. Results also indicate that the circular-bodied configurations exhibit the greatest longitudinal stability and the least direc¬tional stability. Concepts with the variable geometry afterbody contour display the most directional stability and the greatest zero-lift drag.