A Study Of The Simulation Of Flow With Free Stream Mach Number 1 In A Choked Wind Tunnel

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A Study of the Simulation of Flow with Free-stream Mach Number 1 in a Choked Wind Tunnel

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

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A Study of the Simulation of Flow with Free-stream Mach Number 1 in a Choked Wind Tunnel by John R. Spreiter,Donald W. Smith,B. Jeanne Hyett Pdf

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.

A Study of the Simulation of Flow with Free-stream Mach Number 1 in a Choked Wind Tunnel

Author : John R. Spreiter,Donald W. Smith,B. Jeanne Hyett
Publisher : Unknown
Page : 44 pages
File Size : 54,5 Mb
Release : 1960
Category : Aerodynamics
ISBN : NASA:31769000421217

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A Study of the Simulation of Flow with Free-stream Mach Number 1 in a Choked Wind Tunnel by John R. Spreiter,Donald W. Smith,B. Jeanne Hyett Pdf

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.

NASA Technical Report

Author : Anonim
Publisher : Unknown
Page : 60 pages
File Size : 41,7 Mb
Release : 1961
Category : Aerodynamics
ISBN : MINN:30000011021890

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NASA Technical Report by Anonim Pdf

Index to NASA Technical Publications

Author : United States. National Aeronautics and Space Administration
Publisher : Unknown
Page : 128 pages
File Size : 47,6 Mb
Release : 1960-07
Category : Electronic
ISBN : STANFORD:36105024165701

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Index to NASA Technical Publications by United States. National Aeronautics and Space Administration Pdf

Index of NASA Technical Publications

Author : United States. National Aeronautics and Space Administration
Publisher : Unknown
Page : 448 pages
File Size : 44,8 Mb
Release : 1960
Category : Aeronautics
ISBN : UIUC:30112032439504

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Index of NASA Technical Publications by United States. National Aeronautics and Space Administration Pdf

Theoretical Pressure Distributions on Wings of Finite Span at Zero Incidence for Mach Numbers Near 1

Author : Alberta Y. Alksne,John R. Spreiter
Publisher : Unknown
Page : 58 pages
File Size : 42,5 Mb
Release : 1961
Category : Aerodynamics, Transonic
ISBN : NASA:31769000421340

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Theoretical Pressure Distributions on Wings of Finite Span at Zero Incidence for Mach Numbers Near 1 by Alberta Y. Alksne,John R. Spreiter Pdf

A method employed heretofore by the authors to obtain approximate solutions of the transonic flow equation for plane and axisymmetric flow is extended to give reasonable results for wings of finite span, consistent with the known properties of transonic flows. In this method the partial differential equation appropriate to the study of transonic flow is replaced by a nonlinear ordinary differential equation which can be solved by numerical methods. Asymptotic forms of this differential equation are given for very high and very low aspect ratios and analytic results are obtained for certain special cases. Numerical results, calculated by use of electronic computing machines, are given in the form of pressure distribution and pressure drag for two profile shapes, wedge and circular arc, for wings of rectangular plan form. The range of aspect ratios covered extends effectively from zero to infinity and agreement with the asymptotic results is shown at both limits.

NASA Technical Paper

Author : Anonim
Publisher : Unknown
Page : 490 pages
File Size : 43,5 Mb
Release : 1981
Category : Astronautics
ISBN : MINN:31951000586488G

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NASA Technical Paper by Anonim Pdf

Monthly Catalog of United States Government Publications

Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1248 pages
File Size : 42,6 Mb
Release : 1961
Category : Government publications
ISBN : WISC:89038149167

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Monthly Catalog of United States Government Publications by United States. Superintendent of Documents Pdf

Monthly Catalog of United States Government Publications, Cumulative Index

Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1250 pages
File Size : 53,8 Mb
Release : 1979
Category : United States
ISBN : STANFORD:36105022657527

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Monthly Catalog of United States Government Publications, Cumulative Index by United States. Superintendent of Documents Pdf

Applied Mechanics Reviews

Author : Anonim
Publisher : Unknown
Page : 814 pages
File Size : 55,6 Mb
Release : 1968
Category : Mechanics, Applied
ISBN : UCAL:C2682428

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Applied Mechanics Reviews by Anonim Pdf