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Performance Summary And Analysis Of A Mach 3 0 Design Axisymmetric All External Compression Double Cone Inlet Mach Number Range 3 0 To 0 8 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 Summary And Analysis Of A Mach 3 0 Design Axisymmetric All External Compression Double Cone Inlet Mach Number Range 3 0 To 0 8 book. This book definitely worth reading, it is an incredibly well-written.
Author : John L. Allen,Owen H. Davis,Glenn A. Mitchell
Publisher : Unknown
Page : 24 pages
File Size : 46,9 Mb
Release : 1960
Category : Airplanes
ISBN : UIUC:30112106904698
Author : Owen H. Davis,Glenn A. Mitchell
Publisher : Unknown
Page : 36 pages
File Size : 48,8 Mb
Release : 1960
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106904706
Author : Anonim
Publisher : Unknown
Page : 1368 pages
File Size : 48,9 Mb
Release : 1983
Category : Aeronautics
ISBN : UIUC:30112104409468
Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1304 pages
File Size : 49,7 Mb
Release : 1963
Category : Government publications
ISBN : RUTGERS:39030030433173
Author : Anonim
Publisher : Unknown
Page : 20 pages
File Size : 43,6 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000458615
Author : Paul C. Simon,Dennis W. Brown,Ronald G. Huff
Publisher : Unknown
Page : 50 pages
File Size : 52,6 Mb
Release : 1957
Category : Aerodynamics, Supersonic
ISBN : UOM:39015086490482
Author : L. J. Obery,G. W. Englert
Publisher : Unknown
Page : 72 pages
File Size : 42,8 Mb
Release : 1951
Category : Aerodynamics, Supersonic
ISBN : UOM:39015086432005
An experimental investigation to determine the external and internal flow characteristics of a typical ram-jet-inlet configuration of an external-compression type utilizing an isentropic spike and a subsonic diffuser was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel. The model was investigated of a range of mass-flow ratios at angles of attack up to 10 degrees, free-stream Mach numbers of 1.59, 1.79, and 1.99, and a Reynolds number of approximately 2,400,000 based on inlet diameter.
Author : Norman D. Wong
Publisher : Unknown
Page : 68 pages
File Size : 53,6 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 : Leroy L. Presley,William P. Peterson
Publisher : Unknown
Page : 58 pages
File Size : 51,9 Mb
Release : 1960
Category : Aerodynamics
ISBN : UIUC:30112104505299
Author : Maynard I. Weinstein,Joseph Davids,United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 51 pages
File Size : 41,7 Mb
Release : 1951
Category : Aerodynamics, Supersonic
ISBN : OCLC:713834095
An investigation was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet having a conical spike and a supersonic cowl lip. Measurements of lift, drag pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees. The average Reynolds number based on inlet diameter was 2,300,000.
Author : Ione D. V. Faro
Publisher : Unknown
Page : 186 pages
File Size : 50,5 Mb
Release : 1965
Category : Aerodynamics, Supersonic
ISBN : UOM:39015047291615
The design and operation of supersonic inlets is discussed. The means by which the incoming flow may be decelerated to a subsonic velocity are enumerated and evaluated. This report covers diffusers which employ internal compression, external compression or a combination of the two. Experimentally determined values of the total pressure recovery, the capture-area ratio and the inlet drag are compared with those determined from available theories for all types of diffusers. The discussions which in general refer to axisymmetric configurations usually may be applied with equal validity to two-dimensional diffusers. However, some specific problems of the latter are treated. The effects of boundary layer are considered in some detail as are the problems of oscillating flow. (Author).
Author : Scott D. Holland
Publisher : Unknown
Page : 20 pages
File Size : 42,8 Mb
Release : 1993
Category : Electronic
ISBN : NASA:31769000521859
Author : John H. Lundell
Publisher : Unknown
Page : 38 pages
File Size : 41,9 Mb
Release : 1961
Category : Propulsion systems
ISBN : UIUC:30112106742643
Author : Glen A. Mitchell
Publisher : Unknown
Page : 44 pages
File Size : 55,7 Mb
Release : 1968
Category : Vortex generators
ISBN : UIUC:30112106595512
Author : Richard A. Yeager,Laurence W. Gertsma
Publisher : Unknown
Page : 22 pages
File Size : 42,8 Mb
Release : 1958
Category : Rockets (Aeronautics)
ISBN : UOM:39015086464180
