Effects of Vibrational Nonequilibrium on the Inviscid Design of an Axisymmetric Nozzle for Hypersonic Flow PDF Download
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Author: John Benjamin Anders
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 52
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Author: John Benjamin Anders
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 52
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Author: Graham V. Candler
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: James Joe Der
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
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Book Description
Chemical and vibrational nonequilibrium phenomena in steady inviscid flow fields are studied by the analysis of flow past curved boundaries. Possible alternative choices of the state variables to be used are considered. General features of the nonequilibrium flow are studied by examination of the mathematical properties of the nonlinear flow equations. An axisymmetric nonequilibrium flow of air through a supersonic nozzle is analyzed by means of numerical computations. The coupling effects between nonuniformity (across a nozzle section) and nonequilibrium, not taken into account in the quasi-one-dimensional flow approximation, are revealed by the present analysis.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 714
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Author: Wallace D. Hayes
Publisher: Courier Corporation
ISBN: 0486160483
Category : Science
Languages : en
Pages : 628
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Book Description
Unified, self-contained view of nonequilibrium effects, body geometries, and similitudes available in hypersonic flow and thin shock layer; appropriate for graduate-level courses in hypersonic flow theory. 1966 edition.
Author: Thomas Laurence Larsen
Publisher:
ISBN:
Category :
Languages : en
Pages : 81
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Book Description
The study experimentally investigated equilibrium and non-equilibrium flow at the exit of a 9 1/2 inch diameter axisymmetric contoured hypersonic nozzle. The flow was probed with an impact pressure probe, and steady state and transient calorimeters, and the velocity was calculated from these data. The shape of the resulting velocity profiles showed that the nozzle produced uniform parallel flow, and that the nozzle design method was adequate for use in designing a 5.5 foot diameter contoured nozzle to produce equilibrium flow up to Mach 10 and non-equilibrium flow at Mach numbers of 11-15 in an arc-heated hypersonic tunnel. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 542
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1196
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Author: I. R. Hurle
Publisher:
ISBN:
Category : Aerothermodynamics
Languages : en
Pages : 0
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Studies have been made of the extent of vibrational nonequilibrium produced in supersonic expansions of undissociated N2 from known initial equilibrium conditions attained behind reflected shock waves. The N2 was shock heated and compressed to reservoir temperatures and pressures in the ranges 2800 to 4600K, and 24 to 82 atm. It was then allowed to expand through a 15 degree axisymmetric nozzle coupled to the end of the shock tube. The extent of vibrational nonequilibrium was determined by measurements of local vibrational temperatures using the spectrum-line reversal method. The measurements showed the vibrational temperatures in the expansion flows to be much closer to equilibrium than the Landau-Teller relaxation theory predicts. Observations at two area ratios showed that the flow was not completely frozen in the vibrational sense. The probability of N2 vibrational de-excitation inferred from these measurements of vibrational relaxation made behind normal shock waves. Reasons for this apparent difference are discussed in terms of the basic environmental and kinetic differences between shock-wave and nozzle-expansion flows. The validity of the application of Landau-Teller relaxation assumptions and shock-tube measured rates to predict nonequilibrium in expansion flows is thus questioned. (Author).
Author: Wayne Douglas Erickson
Publisher:
ISBN:
Category : Nitrogen
Languages : en
Pages : 54
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Book Description
