An Experimental Investigation of the Effects of Rocket Plume Simulators on the Radial and Longitudinal Pressure Distribution of a Sting Mounted Body of Revolution at Transonic Mach Numbers
CHRYSLER CORP NEW ORLEANS LA MICHOUD DEFENSE-SPACE DIV
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Experimental aerodynamic investigations were conducted at the Cornell Aeronautical Laboratory CAL transonic wind tunnel to determine the effects of several rocket plume simulators on the pressure distribution of a body of revolution. These tests were conducted during September, 1971, on a sting supported model and were extensions of earlier August 1970 tests on similar strut supported models. Therefore, these data can also be utilized to determine the effects of strut mounting on data validity. Local surface pressure data were recorded over an angle of attack range of plus or minus 2 degrees at Mach numbers of 0.9, 1.0 and 1.2 on a four-caliber tangent ogive nose with a cylindrical, a boattailed, and a flared afterbody and on the cylindrical afterbody with either a solid disc or a perpendicular normal jet flow acting as plume simulators.
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