The 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.
Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot
Joint Propulsion Conf. ; 1985 ; Monterey, CA, United States
1985-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Numerical Simulation of Supersonic Inlet Flow with Movable Cowl
Online Contents | 2015
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