Transonic Blockage Investigation of a Proposed Dynamic Wind Tunnel Mount (Model Fly Program, USAF)

摘要

An aerodynamic blockage investigation was conducted on a 1/16-scale model of a dynamic wind tunnel mount proposed for the Propulsion Wind Tunnel, Transonic (16T). The investigation was performed from Mach 0.60 to 1.50. The results are presented in terms of test section wall suction required to establish Mach number and static pressure distributions in the vicinity of the model. A maximum effective model blockage of approximately 4 percent occurred at Mach 1.00 to 1.10. Wall suction requirements were apparently within the maximum suction capabilities available for the Tunnel 16T. No severe pressure disturbances were measured in the proposed model location. (Author)