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02 Scale B 1 External Compression Inlet Verification Model Test At Transonic And Supersonic Mach Numbers
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Book Synopsis 0.2-scale B-1 External-compression Inlet Verification Model Test at Transonic and Supersonic Mach Numbers by : R. C. German
Download or read book 0.2-scale B-1 External-compression Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by R. C. German and published by . This book was released on 1974 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 0.2-scale B-1 External-compression Inlet Verification Model Test at Transonic and Supersonic Mach Numbers by : R. C. German
Download or read book 0.2-scale B-1 External-compression Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by R. C. German and published by . This book was released on 1974 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers by : John F. Riddell
Download or read book Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by John F. Riddell and published by . This book was released on 1972 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Results of a 0.2-Scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers by :
Download or read book Results of a 0.2-Scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Results of a 0.2-Scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers by :
Download or read book Results of a 0.2-Scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Results of a 0.1-scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers by : F. J. Graham
Download or read book Results of a 0.1-scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers written by F. J. Graham and published by . This book was released on 1971 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Results of a 0.1-Scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers by :
Download or read book Results of a 0.1-Scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers written by and published by . This book was released on 1971 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Results of a 0.1-Scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers by :
Download or read book Results of a 0.1-Scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers written by and published by . This book was released on 1971 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Results of a Full-scale B-1 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers by : H. E. McDill
Download or read book Results of a Full-scale B-1 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers written by H. E. McDill and published by . This book was released on 1975 with total page 416 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Results of the Full-scale F-15 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers by : H. E. McDill
Download or read book Results of the Full-scale F-15 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers written by H. E. McDill and published by . This book was released on 1972 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Results of a Full-scale B-1 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers by : H. E. McDill
Download or read book Results of a Full-scale B-1 Inlet/engine Compatibility Test at Subsonic and Supersonic Mach Numbers written by H. E. McDill and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Results of a 0.228-scale RA-5C Inlet Model Test at Transonic and Supersonic Mach Numbers by : H. E. McDill
Download or read book Results of a 0.228-scale RA-5C Inlet Model Test at Transonic and Supersonic Mach Numbers written by H. E. McDill and published by . This book was released on 1969 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79 by : Owen H. Davis
Download or read book Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79 written by Owen H. Davis and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Documentation of the Phase III 0.192-scale Northrop/McDonnell-Douglas F-18 Inlet Performance Test at Mach Numbers 0 to 1.55 by : Jimmy Walker
Download or read book Documentation of the Phase III 0.192-scale Northrop/McDonnell-Douglas F-18 Inlet Performance Test at Mach Numbers 0 to 1.55 written by Jimmy Walker and published by . This book was released on 1978 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Results of a 0.125-scale RA-5C Inlet Model Test at Transonic and Supersonic Mach Numbers by : H. E. McDill
Download or read book Results of a 0.125-scale RA-5C Inlet Model Test at Transonic and Supersonic Mach Numbers written by H. E. McDill and published by . This book was released on 1970 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal by : Earl C. Watson
Download or read book An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal written by Earl C. Watson and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
