Results of 0.2-Scale B-1 Production Inlet Development and Verification Tests at Subsonic and Supersonic Mach Numbers
Final rept. 8 Jul-17 Dec 1974
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Results are presented for a wind tunnel investigation of the 0.2- scale B-1 aircraft inletforebody model during which a production version of the inlet configuration was defined and the performance characteristics verified. The test was conducted at Mach numbers from 0 to 2.3, at angles of attack from - 2 to 13 deg, and at yaw angles from -6 to 6 deg. Performance data are presented primarily in the form of engine-face total-pressure recovery, turbulence index, and various distortion indices as a function of engine-face mass-flow ratio. For the development test phase, results are given that show the effects of reducing the inlet diffuser ramp length, varying the inlet cowl lip contours, changing the inlet bleed porosities, and reducing the inlet bleed discharge area. The performance characteristics of the selected inlet configuration are documented over the Mach number range with inlet geometry as controlled by the individual inlet control sensor schedules as well as by a free-stream Mach number schedule. The effects of control system errors and the aircraft takeoff inlet performance characteristics are also presented.