Results of a 0.1-scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers

Results of a 0.1-scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers
Author: F. J. Graham
Publisher:
Total Pages: 150
Release: 1971
Genre: Airplanes
ISBN:
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Results are presented of a wind tunnel investigation of a 0.1-scale model of the left-hand dual inlet air induction system of the B-1 aircraft. The test was conducted from Mach number 0.55 to 2.2 over an angle-of-attack range from -4 to 13 deg and yaw angles of -8 to 5 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion, and turbulence index is presented as a function of inlet mass-flow ratios for various inlet geometries and model attitudes. The total-pressure recovery of the mixed-compression inlet was very good, but the total-pressure distortion at critical massflow ratios was higher than normally desired for satisfactory turbine engine operation. Best performance was realized with ramp and throat height schedules determined from previous testing. Effects of angle of attack and yaw were seen as general sidewash effects. The addition of canard-type fins had negligible effect on inlet performance. (Author).

Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers

Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers
Author: John F. Riddell
Publisher:
Total Pages: 250
Release: 1972
Genre: Airplanes
ISBN:
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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).

Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers

Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers
Author: L. Stewart Rolls
Publisher:
Total Pages: 22
Release: 1950
Genre: Aeronautics
ISBN:
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The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.

Experimental Dynamic Response of a Two-dimensional, Mach 2.7, Mixed-compression Inlet

Experimental Dynamic Response of a Two-dimensional, Mach 2.7, Mixed-compression Inlet
Author: Robert J. Baumbick
Publisher:
Total Pages: 36
Release: 1972
Genre: Aerodynamics, Supersonic
ISBN:
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A test program was conducted on a two-dimensional supersonic inlet. Internal disturbances in diffuser exit mass flow were produced by oscillating overboard bypass doors. Open-loop dynamic responses of shock position, throat exit and diffuser exit static pressures are presented. The steady-state and dynamic coupling between ducts were also obtained. The experimental results from the two-dimensional inlet are compared to results from a similar size axisymmetric inlet and also to a transfer function synthesis program.