Accession Number:

AD0904446

Title:

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

Personal Author(s):

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

Report Date:

1972-10-01

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

Descriptive Note:

Final rept. 24 Apr-22 Jun 72,

Supplementary Note:

Prepared in cooperation with ARO, Inc., Tullahoma, Tenn., Rept. no. ARO-PWT-TR-72-135.

Pages:

0122

Identifiers:

Communities Of Interest:

Contract Number:

F40600-73-C-0004

File Size:

0.00MB

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