Transonic Wind-tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Several Configurations of the Scout Vehicle and of a Number of Related Models

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 1/15-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).