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Inlet Performance Characteristics Of A Generalized 1 4 Scale Tactical Aircraft Models At Transonic And Supersonic Mach Numbers Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of Inlet Performance Characteristics Of A Generalized 1 4 Scale Tactical Aircraft Models At Transonic And Supersonic Mach Numbers book. This book definitely worth reading, it is an incredibly well-written.
Author : R. F. Lauer (Jr.)
Publisher : Unknown
Page : 164 pages
File Size : 44,9 Mb
Release : 1971
Category : Aerodynamics, Supersonic
ISBN : UOM:39015104952349
Author : Jimmy Walker
Publisher : Unknown
Page : 202 pages
File Size : 46,9 Mb
Release : 1976
Category : Aerodynamics, Supersonic
ISBN : UOM:39015104975605
A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-scale composite inlet model to evaluate configuration factors which affected inlet performance. In addition, flow-field surveys were made at the inlet throat and on the fuselage, forward of the inlet cowl lip. Inlet performance parameters in terms of total-pressure recovery, distortion, and turbulence at the simulated compressor face, as well as compressor face and throat station total-pressure contours and diffuser duct static-pressure distributions are presented for various Mach numbers and angles of attack and sideslip. The basic air induction system consisted of a normal-shock-type inlet with a long splitter plate assembly and was located beneath the wing glove in proximity to the fuselage. The total-pressure recovery for the basic inlet system was slightly better than normal shock recovery for cruise attitudes at supersonic Mach numbers. At Mach numbers approaching 2.0, the basic inlet system was operating close to the buzz limit at design engine airflow. Reductions in total-pressure distortion were achieved by increasing the fuselage-to-inlet standoff distance and by inlet duct boundary-layer blowing. (Author).
Author : Anonim
Publisher : Unknown
Page : 552 pages
File Size : 42,9 Mb
Release : 1978
Category : Airplanes
ISBN : PSU:000011860426
Author : Anonim
Publisher : Unknown
Page : 850 pages
File Size : 40,5 Mb
Release : 2024-07-01
Category : Science
ISBN : CORNELL:31924057185344
Author : Anonim
Publisher : Unknown
Page : 454 pages
File Size : 49,6 Mb
Release : 1975
Category : Aerodynamics
ISBN : CORNELL:31924004261396
Author : Anonim
Publisher : Unknown
Page : 1124 pages
File Size : 42,6 Mb
Release : 1987
Category : Aeronautics
ISBN : UIUC:30112075701448
Author : F. J. Graham
Publisher : Unknown
Page : 150 pages
File Size : 46,8 Mb
Release : 1971
Category : Airplanes
ISBN : UOM:39015104952554
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).
Author : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher : Unknown
Page : 478 pages
File Size : 41,5 Mb
Release : 1968
Category : Aeronautics
ISBN : STANFORD:36105113774298
Author : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher : Unknown
Page : 470 pages
File Size : 53,8 Mb
Release : 1969
Category : Aeronautics
ISBN : CORNELL:31924057848859
Author : Anonim
Publisher : Unknown
Page : 1388 pages
File Size : 55,7 Mb
Release : 1971
Category : Government publications
ISBN : OSU:32437010622500
Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1408 pages
File Size : 48,5 Mb
Release : 1976
Category : United States
ISBN : STANFORD:36105021034173
Author : Anonim
Publisher : Unknown
Page : 1076 pages
File Size : 54,6 Mb
Release : 1978
Category : Research
ISBN : UOM:39015048696630
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.
Author : C. F. Anderson,F. M. Jackson
Publisher : Unknown
Page : 170 pages
File Size : 51,7 Mb
Release : 1972
Category : Airplanes
ISBN : UOM:39015104952414
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
Author : John F. Riddell,F. M. Jackson
Publisher : Unknown
Page : 250 pages
File Size : 44,9 Mb
Release : 1972
Category : Airplanes
ISBN : UOM:39015104952448
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 : Anonim
Publisher : Unknown
Page : 982 pages
File Size : 52,7 Mb
Release : 1990
Category : Aeronautics
ISBN : UIUC:30112075696762
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).
