Analytic Study of Induced Pressure on Long Bodies of Revolution with Varying Nose Bluntness at Hypersonic Speeds PDF Download
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Author: Vernon Van Hise
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 28
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Book Description
Pressure distributions and shock shapes for a series of cylindrical afterbodies having nose fineness ratios from 0.4 to 4 have been calculated by using the method of characteristics for a perfect gas. The fluid mediums investigated were air and helium and the Mach number range was from 5 to 40. Flow parameters obtained from blast-wave theory give a good correlations of blunt-nose induced pressures and shock shapes. Experimental results are found to be in good agreement with the characteristic calculations. The concept of hypersonic similitude enables good correlation of the results with respect to body shape, Mach number, and ratio of specific heats.
Author: Vernon Van Hise
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
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Book Description
A systematic study of induced pressures on a series of bodies of revolution with varying nose bluntness has been made by using the method of characteristics for a perfect gas. The fluid mediums investigated were air and helium and the Mach number range was from 5 to 40. A study of representative shock shapes was also made. Flow parameters obtained from the blast-wave analogy gave good correlations of induced pressures and shock shapes. The induced-pressure correlations yielded empirical equations for air and helium which cover the complete range of nose bluntness considered. (Nose fineness ratios varied from 0.4 to 4.) Available experimental results were in good agreement with the characteristics solutions. Properties connected with the concept of hypersonic similitude enabled correlations of the calculations to be made with respect to nose shape, Mach number, and ratio of specific heats.
Author: Vernon Van Hise
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 28
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Book Description
Pressure distributions and shock shapes for a series of cylindrical afterbodies having nose fineness ratios from 0.4 to 4 have been calculated by using the method of characteristics for a perfect gas. The fluid mediums investigated were air and helium and the Mach number range was from 5 to 40. Flow parameters obtained from blast-wave theory give a good correlations of blunt-nose induced pressures and shock shapes. Experimental results are found to be in good agreement with the characteristic calculations. The concept of hypersonic similitude enables good correlation of the results with respect to body shape, Mach number, and ratio of specific heats.
Author: Vernon van Hise
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Book Description
Author: Vernon Van Hise
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
![Analytical Study of Induced Pressure on Long Bodies of Revolution with Varying Nose Bluntness at Hypersonic Speeds [with List of References] PDF](https://books.google.com/books/content/images/frontcover/YzuswgEACAAJ?fife=w80-h100)
Author:
Publisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 18
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 28
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Book Description
Author:
Publisher: Academic Press
ISBN: 0080563856
Category : Technology & Engineering
Languages : en
Pages : 339
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Book Description
Advances in Applied Mechanics
Author: F.R. Riddell
Publisher: Elsevier
ISBN: 0323142621
Category : Transportation
Languages : en
Pages : 769
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Book Description
Progress in Astronautics and Rocketry, Volume 7: Hypersonic Flow Research compiles papers presented at a conference on hypersonics held at the Massachusetts Institute of Technology in August 1961. This book discusses the low Reynolds number effects, chemical kinetics effects, inviscid flow calculations, and experimental techniques relating to the problems in acquiring an understanding of hypersonic flow. The structure and composition of hypersonic wakes with attendant complex chemical kinetic effects is only briefly mentioned. This text consists of five parts. Parts A to C comprise of theoretical papers on the problems of calculating flow fields at hypersonic speeds. The experimental techniques that are of immediate practical interest in view of the difficulty of flight testing are discussed in Parts D and E. This publication is beneficial to engineers involved in advanced design problems.
Author: A. B. Bailey
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 72
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Book Description
An experimental investigation was made to determine the pressure distribution, shock shape, and shock detachment distance for spheres and the latter two characteristics for flatfaced bodies in a heated argon flow. The modified Newtonian approximation for the pressure distribution, which is strictly an empirical relationship, gives good results when applied to the first 60 degrees of a hemisphere under conditions where the body boundary layer and the shock layer merge. The natural flow visualization produced as a result of the high total temperature and consequent excitation of the argon enabled this study to be made. Photographs taken of the shocks generated by a series of spheres and flat-faced bodies were analyzed with a photo-densitometer to determine the shock shape and shock detachment distance. The blast analogy predicts a difference in the shape of shocks in argon and air at high Mach numbers and Reynolds numbers. An empirical relationship proposed by Love was used to calculate the shock shape in air for Mach numbers corresponding to those of the present investigation. (Author).
Author: Michael H. Bertram
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 58
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Book Description
