A preliminary investigation of a swept, rectangular, supersonic scoop inlet designed to have low external drag at the design Mach num¬ber of 2.7 has been conducted at the Langley Aeronautical Laboratory. The inlet was tested with two simulated fuselages having circular and rectangular cross sections. Various methods of boundary-layer removal were employed with the rectangular-fuselage configuration. Pressure-recovery and mass-flow data are presented for angles of attack of -5°, 0°, and 5° at Mach numbers of 2.03 and 2.71. A few results were obtained at a Mach number of 3.12 for the simulated fuselage of circular cross section.
展开▼
