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Wind Tunnel Investigation Of Three Axisymmetric Cowls Of Different Lengths At Mach Numbers From 0 60 To 0 92 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 Wind Tunnel Investigation Of Three Axisymmetric Cowls Of Different Lengths At Mach Numbers From 0 60 To 0 92 book. This book definitely worth reading, it is an incredibly well-written.
Author : Richard J. Re
Publisher : Unknown
Page : 292 pages
File Size : 47,8 Mb
Release : 1993
Category : Airplanes
ISBN : NASA:31769000522436
Author : Anonim
Publisher : Unknown
Page : 1072 pages
File Size : 54,7 Mb
Release : 1994
Category : Science
ISBN : MSU:31293011519174
Author : Anonim
Publisher : Unknown
Page : 392 pages
File Size : 52,8 Mb
Release : 1994
Category : Electronic
ISBN : NASA:31769000659386
Author : Anonim
Publisher : Unknown
Page : 1374 pages
File Size : 42,5 Mb
Release : 1994
Category : Government publications
ISBN : OSU:32437010530166
Author : Frederick K. Hube,Leroy M. Jenke
Publisher : Unknown
Page : 278 pages
File Size : 42,8 Mb
Release : 1970
Category : Aerodynamics, Supersonic
ISBN : UOM:39015104952224
Author : John L. Allen,Owen H. Davis,Glenn A. Mitchell
Publisher : Unknown
Page : 24 pages
File Size : 52,9 Mb
Release : 1960
Category : Airplanes
ISBN : UIUC:30112106904698
Author : Anonim
Publisher : Unknown
Page : 128 pages
File Size : 48,5 Mb
Release : 1951
Category : Government publications
ISBN : WISC:89117116087
Author : John R. Spreiter,Donald W. Smith,B. Jeanne Hyett
Publisher : Unknown
Page : 44 pages
File Size : 53,9 Mb
Release : 1960
Category : Aerodynamics
ISBN : UIUC:30112106632042
Summary: The degree to which experimental results obtained under choking conditions in a wind tunnel with solid walls simulate those associated with an unbounded flow with free-stream Mach number 1 is investigated for the cases of two-dimensional and axisymmetric flows. It is found that a close resemblance does indeed exist in the vicinity of the body, and that the results obtained in this way are generally at least as accurate as those obtained in a transonic wind tunnel with partly open test section. Some of the results indicate, however, that substantial interference effects, particularly those of the wave reflection type, may be encountered under certain conditions, both in choked wind tunnels and in transonic wind tunnels, and that the reduction of these interference effects to acceptable limits may require the use of models of unusually small size.
Author : Donald B. Smeltzer,Norman E. Sorensen
Publisher : Unknown
Page : 252 pages
File Size : 45,9 Mb
Release : 1970
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106880799
Author : A. B. Blair
Publisher : Unknown
Page : 108 pages
File Size : 44,8 Mb
Release : 1978
Category : Electronic
ISBN : UIUC:30112106564633
Author : Anonim
Publisher : Unknown
Page : 48 pages
File Size : 44,7 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000459316
Author : Anonim
Publisher : Unknown
Page : 40 pages
File Size : 47,5 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000459993
Author : Francis J. Capone
Publisher : Unknown
Page : 308 pages
File Size : 47,6 Mb
Release : 1980
Category : Electronic
ISBN : NASA:31769000431075
Author : Anonim
Publisher : Unknown
Page : 1312 pages
File Size : 47,6 Mb
Release : 1968
Category : Electronic
ISBN : IND:30000128341256
Author : Edward Przebienda
Publisher : Unknown
Page : 1298 pages
File Size : 53,5 Mb
Release : 1971
Category : Government publications
ISBN : MINN:31951T00218132Y
