DISTORTION IN A FULL-SCALE BICONE INLET WITH INTERNAL FOCUSED COMPRESSION AND 45 PERCENT INTERNAL CONTRACTION

摘要

An experimental investigation was made to determine the distortion characteristics at the sub¬sonic diffuser exit of a full-scale, Mach 2.5, axisymmetric, mixed compression inlet. Per¬formance and steady-state distortion characteristics were obtained at zero and maximum angle-of-attack and during an inlet unstart-restart sequence. For the configuration with no cowl bleed, steady-state distortion (Pmax-Pmin)/P ranged from 0.10 for critical inlet operation at 0° angle-of-attack to 0.306 for supercritical inlet operation at 6.84 angle-of-attack. Vortex generators provided a 50 percent reduction in steady-state distortion for critical op¬eration. Bleed has a smaller effect on steady-state distortion.