An experimental investigation was conducted to determine the effect of design changes on the aerodynamic and acoustic performance of translating-centerbody sonic inlets. Scale-model inlets with a diffuser exit diameter of 30.48 centimeters (12 in.) were tested in the Lewis Research Center's 2. 74- by 4.58-meter (9- by 15-ft) V/STOL wind tunnel. The effects of centerbody position, entry lip contraction ratio, diffuser length, and diffuser area ratio on inlet total-pressure recovery, distortion, and noise suppression were investigated at static conditions and at a forward velocity of 41 meters per second (80 knots) over a range of incidence angles from 0° to 50°.
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