Results Of A 0 2 Scale B 1 Inlet Verification Model Test At Transonic And Supersonic Mach Numbers

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Results Of A 0 2 Scale B 1 Inlet Verification Model Test At Transonic And Supersonic Mach Numbers

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Author : John F. Riddell
language : en
Publisher:
Release Date : 1972

Results Of A 0 2 Scale B 1 Inlet Verification Model Test At Transonic And Supersonic Mach Numbers written by John F. Riddell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1972 with Airplanes categories.

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).

Results Of A 0 2 Scale B 1 Inlet Verification Model Test At Transonic And Supersonic Mach Numbers

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Author :
language : en
Publisher:
Release Date : 1972

Results Of A 0 2 Scale B 1 Inlet Verification Model Test At Transonic And Supersonic Mach Numbers written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1972 with categories.

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).

0 2 Scale B 1 External Compression Inlet Verification Model Test At Transonic And Supersonic Mach Numbers

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Author : R. C. German
language : en
Publisher:
Release Date : 1974

0 2 Scale B 1 External Compression Inlet Verification Model Test At Transonic And Supersonic Mach Numbers written by R. C. German and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Jet engines categories.

Results Of A 0 2 Scale B 1 Inlet Verification Model Test At Transonic And Supersonic Mach Numbers

DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1972

Results Of A 0 2 Scale B 1 Inlet Verification Model Test At Transonic And Supersonic Mach Numbers written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1972 with categories.

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).

Results Of A 0 1 Scale B 1 Inlet Model Test At Transonic And Supersonic Mach Numbers

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Author : F. J. Graham
language : en
Publisher:
Release Date : 1971

Results Of A 0 1 Scale B 1 Inlet Model Test At Transonic And Supersonic Mach Numbers written by F. J. Graham and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Airplanes categories.

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 0 2 Scale B 1 Production Inlet Development And Verification Tests At Subsonic And Supersonic Mach Numbers

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Author : R. F. Lauer (Jr.)
language : en
Publisher:
Release Date : 1975

Results Of 0 2 Scale B 1 Production Inlet Development And Verification Tests At Subsonic And Supersonic Mach Numbers written by R. F. Lauer (Jr.) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Turbulence categories.

0 2 Scale B 1 External Compression Inlet Verification Model Test At Transonic And Supersonic Mach Numbers

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Author : R. C. German
language : en
Publisher:
Release Date : 1974

0 2 Scale B 1 External Compression Inlet Verification Model Test At Transonic And Supersonic Mach Numbers written by R. C. German and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Jet engines categories.

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
language : en
Publisher:
Release Date : 1975

Results Of A Full Scale B 1 Inlet Engine Compatibility Test At Subsonic And Supersonic Mach Numbers written by H. E. McDill and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Jet engines categories.

Results Of A 0 1 Scale B 1 Inlet Model Test At Transonic And Supersonic Mach Numbers

DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1971

Results Of A 0 1 Scale B 1 Inlet Model Test At Transonic And Supersonic Mach Numbers written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with categories.

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 1 Scale B 1 Inlet Model Test At Transonic And Supersonic Mach Numbers

DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1971

Results Of A 0 1 Scale B 1 Inlet Model Test At Transonic And Supersonic Mach Numbers written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with categories.

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).