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Experimental Aerodynamic Characteristics For Slender Bodies With Thin Wings And Tail At Angles Of Attack From 0 To 58 And Mach From 0 6 To 2 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 Experimental Aerodynamic Characteristics For Slender Bodies With Thin Wings And Tail At Angles Of Attack From 0 To 58 And Mach From 0 6 To 2 0 book. This book definitely worth reading, it is an incredibly well-written.
Author : Leland H. Jorgensen,Edgar R. Nelson
Publisher : Unknown
Page : 164 pages
File Size : 45,6 Mb
Release : 1976
Category : Aerodynamics
ISBN : UIUC:30112101592506
Author : Leland Howard Jorgensen
Publisher : Unknown
Page : 132 pages
File Size : 45,7 Mb
Release : 1976
Category : Aerodynamics
ISBN : UIUC:30112101592498
Author : Anonim
Publisher : Unknown
Page : 732 pages
File Size : 50,7 Mb
Release : 1975
Category : Aeronautics
ISBN : MINN:31951000844901B
Author : Anonim
Publisher : Unknown
Page : 1388 pages
File Size : 53,6 Mb
Release : 1971
Category : Government publications
ISBN : OSU:32437010622500
Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1408 pages
File Size : 49,8 Mb
Release : 1976
Category : United States
ISBN : STANFORD:36105021034173
Author : Anonim
Publisher : Unknown
Page : 742 pages
File Size : 42,9 Mb
Release : 1976
Category : Aeronautics
ISBN : UOM:39015057253273
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author : Daniel W. Lester
Publisher : Unknown
Page : 578 pages
File Size : 55,5 Mb
Release : 1980
Category : Government publications
ISBN : UCSC:32106020209349
Author : Robert J. Krieger,J. E. Gregoire,R. F. Hood,E. A. Eiswirth,M. L. Taylor
Publisher : Unknown
Page : 136 pages
File Size : 49,5 Mb
Release : 1980
Category : Cruise missiles
ISBN : UOM:39015095299122
This report presents the results of a program that investigated aerodynamic configuring as a method of improving long range supersonic cruise and maneuvering missile performance. Non-circular body, lifting body, blended wing body, wing-body and favorable interference concepts were developed and wind tunnel tested. Substantial improvements in cruise range were shown to result from aero configuring.
Author : Aeronautical Society of India
Publisher : Unknown
Page : 384 pages
File Size : 47,9 Mb
Release : 1988
Category : Aeronautics
ISBN : UOM:39015016523451
Author : Anonim
Publisher : Unknown
Page : 524 pages
File Size : 54,8 Mb
Release : 1977
Category : Aeronautics
ISBN : UIUC:30112075701117
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).
Author : Anonim
Publisher : Unknown
Page : 146 pages
File Size : 44,7 Mb
Release : 1977
Category : Electronic
ISBN : NASA:31769000535446
Author : Society of Automotive Engineers
Publisher : Unknown
Page : 976 pages
File Size : 55,8 Mb
Release : 1980
Category : Aeronautics
ISBN : UCSD:31822015382930
Beginning in 1985, one section is devoted to a special topic
Author : Anonim
Publisher : Unknown
Page : 1014 pages
File Size : 54,8 Mb
Release : 1966-11
Category : Science
ISBN : NYPL:33433066455514
Author : Leland Howard Jorgensen
Publisher : Unknown
Page : 88 pages
File Size : 40,5 Mb
Release : 1975
Category : Aerodynamics
ISBN : UIUC:30112106563718
An experimental investigation was conducted in the Ames 6- by 6-Foot Wind Tunnel to measure the static aerodynamic characteristics for two bodies of elliptic cross section and for their equivalent body of revolution. The equivalent body of revolution had the same length and axial distribution of cross-sectional area as the elliptic bodies. It consisted of a tangent ogive nose of fineness ratio 3 followed by a cylinder with a fineness ratio of 7. For the first body of elliptic cross section, the ratio of the semimajor axis to semiminor axis was held constant at 2 all along the body length. For the second elliptic body the nose was unchanged, but the aftersection was changed as follows: The cross-sectional axis ratio a/b was decreased from 2 to 1 over an axial distance of about 1.66 diam. Then, at this position, the a,b axis system was rotated 900, and the a/b ratio was increased back to 2 over the next 2.34 diam in length. Over the last length of three body diam, this rotated a/b ratio was held constant at 2.
Author : Anonim
Publisher : Unknown
Page : 1150 pages
File Size : 46,5 Mb
Release : 1977
Category : Research
ISBN : UOM:39015048728185
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.