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TRANSONIC WIND-TUNNEL INVESTIGATION OF THE STATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF SEVERAL CONFIGURATIONS OF THE SCOUT VEHICLE AND OF A NUMBER OF RELATED MODELS
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C
Tests were conducted in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.40 to 1.20 and Reynolds numbers per foot of approximately 3.8 x 10 to the 6th power to determine the static longitudinal aerodynamic characteristics of a 115-scale model of the Scout vehicle and of several related configurations. Results are presented which show, for various models, the effects of fin planform, protuberances, an afterbody flare, and a variation in second-stage transition-flare angle. Author