Investigation of Two Bifurcated-Duct Inlet Systems From Mach 0 to 2.0 Over a Wide Ran of Angles of Attack

摘要

A 15.354-percent-scale lightweight fighter-type inlet/forebody was tested in the Ames Unitary Plan Wind Tunnels over a Mach number range of 0 to 2.0. Model configurations consisted of side-mounted normal shock and fixed overhead ramp-type inlets. Each configuration consisted of two inlets ducted (bifurcated) to supply a single engine face. The normal shock inlet variables included a boundary layer splitter bleed system, alternate boundary-layer splitter plates, alternate upper and lower cowl lip shapes, and a blow-in-door (auxiliary inlet) in one lower lip. The only variable of the fixed overhead amp inlet was the boundary layer bleed flow. Reynolds numbers ranged from 1.6×106 to 19.5 x 106/m (2.5 x 106 to 6.4 x lO6/ft). Angle of attack ranged from -10° to 35° and angle of sideslip from -8° to 8°. Test measurements included engine face total pressure recovery, steady-state distortion, dynamic distortion, and surface static pressures on the forebody and inlet surfaces. This report includes only representative data of some of the important para¬meters. A complete listing of the tabulated data is available from NASA-Ames Research Center, Moffett Field, California.