Experimental Surface Pressure Distributions on Three Bodies of Revolution at Mach Numbers from 0.7 to 2.02
NAVAL WEAPONS CENTER CHINA LAKE CA
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Wind tunnel tests were conducted to measure surface pressure distributions on three bodies of revolution at Mach numbers from 0.7 to 2.02 and angle of attack from 10 to -10 degrees. The three bodies were based on the same ogive-cylinder, with one having a sharp nose and the other two being spherically tipped. Surface pressure distributions are presented, along with expressions relating the flow angle to the pressure difference across the spherical nose caps.