Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slotThe experimental low-speed aerodynamic characteristics of an axisymmetric mixed-compression supersonic inlet with variable cowl slot are described. The model consisted of the NASA P-inlet centerbody and redesigned cowl with variable cowl slot powered by the JT8D single-stage fan simulator and driven by an air turbine. The model was tested in the NASA Lewis Research Center 9- by 15-foot low-speed tunnel at Mach numbers of 0, 0.1, and 0.2 over a range of flows, cowl slot openings, centerbody positions, and angles of attack. The variable cowl slot was effective in minimizing lip separation at high velocity ratios, showed good steady-state and dynamic distortion characteristics, and had good angle-of-attack tolerance.
Document ID
19850058668
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Powell, A. G. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Welge, H. R. (Douglas Aircraft Co. Long Beach, CA, United States)
Trefny, C. J. (NASA Lewis Research Center Cleveland, OH, United States)