Results of 0.2-Scale B-1Production Inlet Development and Verification Tests at Subsonic and Supersonic Mach Numbers.

摘要

Results are presented for a wind tunnel investigation of the 0.2-scale B-1aircraft inlet/forebody 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 0to 2.3,at angles of attack from -2to 13deg,and at yaw angles from -6to 6deg. 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. (Author)