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 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 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 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 Scientific and Technical Aerospace Reports written by and published by . This book was released on 1975 with total page 978 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Tests of a Mixed Compression Axisymmetric Inlet with Large Transonic Mass Flow at Mach Numbers 0 6 to 2 65 written by Donald B. Smeltzer and published by . This book was released on 1972 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 38.8-cm (15.28-in.) capture diameter model of a mixed-compression axisymmetric inlet system with a translating cowl was designed and tested. The internal contours, designed for Mach number 2.65, provided a throat area of 59 percent of the capture area when the cowl was retracted for transonic operation. Other model features included a boundary-layer removal system, vortex generators, an engine airflow bypass system, cowl support struts, and rotating rakes at the engine face. All tunnel testing was conducted at a tunnel total pressure of about 1 atm (a unit Reynolds number of about 8.53 million/m at Mach number 2.65) at angles of attack from 0 deg to 4 deg. Results for the following were obtained: total-pressure recovery and distortion at the engine face as a function of bleed mass-flow ratio, the effect of bleed and vortex generator configurations on pressure recovery and distortion, inlet tolerance to unstart due to changes in angle of attack or Mach number, surface pressure distributions, boundary-layer profiles, and transonic additive drag. At Mach number 2.65 and with the best bleed configurations, maximum total pressure recovery at the engine face ranged from 91 to 94.5 percent with bleed mass-flow ratios from 4 to 9 percent, respectively, and total-pressure distortion was less than 10 percent. At off-design supersonic Mach numbers above 1.70, maximum total-pressure recoveries and corresponding bleed mass flows were about the same as at Mach number 2.65, with about 10 to 15 percent distortion. In the transonic Mach number range, total pressure recovery was high (above 96 percent) and distortion was low (less than 15 percent) only when the inlet mass-flow ration was reduced 0.02 to 0.06 from the maximum theoretical value (0.590 at Mach number 1.0).
Download or read book Aeronautical Engineering written by and published by . This book was released on 1985 with total page 586 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
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 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 Performance of External compression Bump Inlet at Mach Numbers of 1 5 to 2 0 written by Paul C. Simon and published by . This book was released on 1957 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Index written by and published by . This book was released on 1975 with total page 1074 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of a Large scale Two dimensional Mixed compression Inlet System written by Norman D. Wong and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.
Download or read book NASA SP written by and published by . This book was released on 1985 with total page 592 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering A Cumulative Index to the 1984 Issues of the Continuing Bibliography written by and published by . This book was released on 1985 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Inlet Spillage Drag Tests and Numerical Flow field Analysis at Subsonic and Transonic Speeds of a 1 8 scale Two dimensional External compression Variable geometry Supersonic Inlet Configuration written by J. E. Hawkins and published by . This book was released on 1976 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Tests of a Small scale NACA Submerged Inlet at Transonic Mach Numbers written by L. Stewart Rolls and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.
