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Performance Of Centerbody Vortex Generators In An Axisymmetric Mixed Compression Inlet At Mach Numbers From 2 0 To 3 0 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 Performance Of Centerbody Vortex Generators In An Axisymmetric Mixed Compression Inlet At Mach Numbers From 2 0 To 3 0 book. This book definitely worth reading, it is an incredibly well-written.
Author : Glen A. Mitchell
Publisher : Unknown
Page : 44 pages
File Size : 51,9 Mb
Release : 1968
Category : Vortex generators
ISBN : UIUC:30112106595512
Author : Donald B. Smeltzer,Norman E. Sorensen
Publisher : Unknown
Page : 252 pages
File Size : 41,8 Mb
Release : 1970
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106880799
Author : Anonim
Publisher : Unknown
Page : 1384 pages
File Size : 48,5 Mb
Release : 1971
Category : Aeronautics
ISBN : UOM:39015000971518
Author : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher : Unknown
Page : 478 pages
File Size : 50,9 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 : 46,6 Mb
Release : 1969
Category : Aeronautics
ISBN : CORNELL:31924057848859
Author : Anonim
Publisher : Unknown
Page : 232 pages
File Size : 55,8 Mb
Release : 1974
Category : Aeronautics
ISBN : MINN:31951000844883N
Author : David A. Choby
Publisher : Unknown
Page : 68 pages
File Size : 53,5 Mb
Release : 1971
Category : Aerodynamics
ISBN : NASA:31769001179913
Author : Norman D. Wong
Publisher : Unknown
Page : 68 pages
File Size : 50,9 Mb
Release : 1971
Category : Jet engines
ISBN : UIUC:30112106747188
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.
Author : Donald B. Smeltzer,Norman E. Sorensen
Publisher : Unknown
Page : 196 pages
File Size : 53,5 Mb
Release : 1972
Category : Aerodynamics, Transonic
ISBN : UIUC:30112106640870
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).
Author : Anonim
Publisher : Unknown
Page : 1498 pages
File Size : 45,8 Mb
Release : 1968
Category : Aeronautics
ISBN : CUB:U183019691046
Author : Harvey E. Neumann
Publisher : Unknown
Page : 52 pages
File Size : 44,6 Mb
Release : 1975
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106566885
Author : Donald B. Smeltzer,Norman E. Sorensen
Publisher : Unknown
Page : 162 pages
File Size : 55,8 Mb
Release : 1968
Category : Jet engines
ISBN : UIUC:30112106914218
Author : Anonim
Publisher : Unknown
Page : 460 pages
File Size : 53,8 Mb
Release : 1962
Category : Aeronautics
ISBN : MINN:30000011045519
Author : Anonim
Publisher : Unknown
Page : 1194 pages
File Size : 46,9 Mb
Release : 1969
Category : Medicine
ISBN : STANFORD:36105026875745
Author : Anonim
Publisher : Unknown
Page : 28 pages
File Size : 43,9 Mb
Release : 1966
Category : Electronic
ISBN : NASA:31769000666456
