Aerodynamic Characteristics of Two Bodies of Revolution with Noses of Varying Spherical Bluntness at Mach Numbers from 0.6 to 1.5
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A wind tunnel investigation was conducted to determine the static stability characteristics of two bodies of revolution fitted with 2-, 3-, and 4- cal tangent ogive noses of varying spherical bluntness. Testing was conducted at Mach numbers from 0.6 to 1.5 and angles of attack from -2 to 14 deg. The major effect of blunting the noses was evidenced in the axial-force coefficient. Lengthening the noses from 2 to 4 cal caused a forward movement of the center- of-pressure location and a corresponding decrease in axial-force coefficient at Mach numbers of 1.0 and higher. Changing from a 5- to a 9-cal midbody resulted in an increase in axial-force coefficient and an aft movement of the center-of- pressure location.
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