Results Of A Full Scale B 1 Inlet Engine Compatibility Test At Subsonic And Supersonic Mach Numbers
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Author | : H. E. McDill |
Publisher | : |
Total Pages | : 416 |
Release | : 1975 |
Genre | : Jet engines |
ISBN | : |
Download Results of a Full-scale B-1 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers Book in PDF, Epub and Kindle
Author | : H. E. McDill |
Publisher | : |
Total Pages | : 0 |
Release | : 1975 |
Genre | : Jet engines |
ISBN | : |
Download Results of a Full-scale B-1 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers Book in PDF, Epub and Kindle
Author | : H. E. McDill |
Publisher | : |
Total Pages | : 330 |
Release | : 1972 |
Genre | : Eagle (Jet fighter plane) |
ISBN | : |
Download Results of the Full-scale F-15 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers Book in PDF, Epub and Kindle
Author | : R. F. Lauer (Jr.) |
Publisher | : |
Total Pages | : 304 |
Release | : 1975 |
Genre | : Turbulence |
ISBN | : |
Download Results of 0.2-scale B-1 Production Inlet Development and Verification Tests at Subsonic and Supersonic Mach Numbers Book in PDF, Epub and Kindle
Author | : H. E. McDill |
Publisher | : |
Total Pages | : 0 |
Release | : 1972 |
Genre | : Eagle (Jet fighter plane). |
ISBN | : |
Download Results of the Full-scale F-15 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers Book in PDF, Epub and Kindle
Author | : John F. Riddell |
Publisher | : |
Total Pages | : 250 |
Release | : 1972 |
Genre | : Airplanes |
ISBN | : |
Download Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers Book in PDF, Epub and Kindle
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).
Author | : Richard A. Martin |
Publisher | : |
Total Pages | : 52 |
Release | : 1971 |
Genre | : Airplanes |
ISBN | : |
Download Comparisons of In-flight F-111A Inlet Performance for On- and Off-scheduled Inlet Geometry at Mach Numbers of 0.68 to 2.18 Book in PDF, Epub and Kindle
In-flight F-111 data on total and static pressure from left inlet during automatically scheduled and manually controlled off-schedule positioning of spike at Mach 0.68 to 2.18.
Author | : |
Publisher | : |
Total Pages | : 450 |
Release | : 1971 |
Genre | : |
ISBN | : |
Download NASA Technical Note Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 352 |
Release | : 1993 |
Genre | : |
ISBN | : |
Download Bibliography on Propulsion Airframe Integration Technologies for High-speed Civil Transport Applications, 1980-1991 Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 0 |
Release | : 1972 |
Genre | : |
ISBN | : |
Download Results of a 0.2-Scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers Book in PDF, Epub and Kindle
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).