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).
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).
Download or read book 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 published by . This book was released on 1975 with total page 304 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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).
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:
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).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on with total page 994 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Blockage Study of a 1 16 scale B 1 Inlet Model in the 1 ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility written by C. F. Anderson and published by . This book was released on 1972 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 1-ft Aerodynamic Wind Tunnels (1T and 1S) of the Propulsion Wind Tunnel Facility to obtain estimates of the performance available for the full-scale B-1 inlet/engine tests in the 16-ft Propulsion Wind Tunnels (16T and 16S). Data were obtained with two nacelle configurations and four wing configurations. The maximum test section blockage was 17 percent. Data were obtained at Mach numbers from 0.55 to 1.30 and from 1.71 to 2.30. The tunnel performance for each configuration was evaluated relative to the others and with regard to the capabilities of the 16-ft tunnels. The results of these tests indicate that the available tunnel performance is significantly compromised with the nacelle configuration which has been selected for the full-scale test. The maximum Mach number estimated to be available for the full-scale test in Tunnel 16T is 1.0. To obtain a full range of engine operating points, however, testing should be restricted to M
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1981 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 850 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 306 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Annual Index written by and published by . This book was released on 1978 with total page 1062 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
Download or read book Results of 0 2 Scale B 1 Production Inlet Development and Verification Tests at Subsonic and Supersonic Mach Numbers written by and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for a wind tunnel investigation of the 0.2- scale B-1 aircraft inlet/forebody model during which a production version of the inlet configuration was defined and the performance characteristics verified. The test was conducted at Mach numbers from 0 to 2.3, at angles of attack from - 2 to 13 deg, and at yaw angles from -6 to 6 deg. Performance data are presented primarily in the form of engine-face total-pressure recovery, turbulence index, and various distortion indices as a function of engine-face mass-flow ratio. For the development test phase, results are given that show the effects of reducing the inlet diffuser ramp length, varying the inlet cowl lip contours, changing the inlet bleed porosities, and reducing the inlet bleed discharge area. The performance characteristics of the selected inlet configuration are documented over the Mach number range with inlet geometry as controlled by the individual inlet control sensor schedules as well as by a free-stream Mach number schedule. The effects of control system errors and the aircraft takeoff inlet performance characteristics are also presented.
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:
Download or read book Bibliography on Propulsion Airframe Integration Technologies for High speed Civil Transport Applications 1980 1991 written by and published by . This book was released on 1993 with total page 352 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Reference Publication written by and published by . This book was released on 1977 with total page 754 pages. Available in PDF, EPUB and Kindle. Book excerpt:
