Results of a Transonic Wind Tunnel Investigation of Thrust Effects on the Aerodynamics of Four Longitudinally-Supported Ringtail Missile Configurations.

摘要

Transonic wind tunnel tests were conducted on a strut-supported model to determine thrust effects on four longitudinal strut supported ringtail configurations. The configurations were achieved by varying the distance between the nozzle exit plane and the ringtail. Thrust was simulated by cold air and was varied from 0to 400pounds. Of primary interest,was the effect of thrust level and longitudinal position of the nozzle exit plane on missile stability. For the thrust levels tested, a favorable effect on longitudinal stability was experienced on the configuration with the nozzle exit plane located at the ringtail leading edge. The test was conducted at the Calspan Corporation's 8foot Transonic Wind Tunnel at Mach numbers ranging from 0.4to 1.2. Angles of attack were from -5degrees to +6degrees at a sideslip angle of 0degrees. Thrust,from 0to 400pounds,was the only varying parameter. (Author)