Accession Number : AD0904446

Title :   Results of a 0.2-Scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers.

Descriptive Note : Final rept. 24 Apr-22 Jun 72,

Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

Personal Author(s) : Riddell, John F.

Report Date : OCT 1972

Pagination or Media Count : 122

Abstract : Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author)

Descriptors :   (*TURBOJET INLETS, JET BOMBERS), WIND TUNNEL MODELS, TRANSONIC FLOW, SUPERSONIC FLOW, JET ENGINE NACELLES, ANGLE OF ATTACK, YAW, BOUNDARY LAYER CONTROL, BLEED SYSTEMS, TURBULENCE, PRESSURE, REYNOLDS NUMBER, MACH NUMBER, PERFORMANCE(ENGINEERING).

Subject Categories : Aerodynamics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE