The Shock Shape and Shock Detachment Distance for Spheres and Flat-faced Bodies in Low-density, Hypervelocity, Argon Flow PDF Download
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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: A. B. Bailey
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 72
Get Book Here
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:
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ISBN:
Category : Magnetohydrodynamics
Languages : en
Pages : 188
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 516
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1180
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 438
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Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 1148
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Author:
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ISBN:
Category : Government publications
Languages : en
Pages : 1160
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Author: United States. Department of Commerce. Office of Technical Services
Publisher:
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Category : Government publications
Languages : en
Pages : 836
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 466
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Author: A. A. Sonin
Publisher: Institute for Aerospace Studies, University of Toronto
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 176
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Book Description
Experiments were performed in an RF generated, low density plasma flow to determine the behaviour of small, cylindrical Langmuir probes in high-speed flows. All mean free paths were large compared to the probe diameter except the mean free path for ion-ion collisions. The tests indicated that under simulated static conditions (probe axis parallel to flow velocity), the theory of Laframboise represented the ion current characteristic well when the ratio between radius of probe and Debye length was large, but not when the probe radius was comparable to or smaller than the Debye length. The results indicated clearly that the ion current decreased with increasing normal velocity, reached a minimum, and then increased again for subsequent increases in velocity. Subsequently, the probes were used in a study of the charged particle number density and electron temperature distributions in the stagnation region of a flat-nosed cylinder in supersonic flow. The electron temperature had a constant value throughout the bow shock and the entire shock layer. The charged particle number density distribution measurements provided a graphic demonstration of the merging of the bow shock and the boundary layer at a value of Reynolds number of about 100, and also furnished evidence of the diffusive separation of the ions and atoms in the shock wave. Independent measurements of the ion flux to the stagnation point wall were in good agreement with the Langmuir probe measurements in the shock layer.
