Abstract:
Mean pressure recovery, distortion and the extent of stable subcritical flow have been measured at zero incidence on a fuselage side intake having a wedge compression surface. The intake was separated from the fuselage by a boundary layer diverter, and had a bleed on the compression surface just inside the entry plane. It was tested with and without bleed having top and bottom swept endwalls on, top endwalls on, and both endwalls off. Detailed measurements of duct total pressure were made at 1.8 times the capture height downstream of the inlet plane for all configurations. Removal of the endwalls leads to an increase in the uniformity of pressure distribution and to an increase in the range of stable subcritical flow.
