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THE WEAK INTERACTION THEORY FOR HYPERSONIC FLOW OVER CONES

The weak interaction effect on cone surface pressures was measured and found to be in good agreement with theory. Correlation was established at a nominal Mach number of 14 with the value of the hypersonic interaction parameter, based on free-stream conditions, ranging from 4 to 20. By using an inve...

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Main Authors:	Hoelmer,Werner, Saarlas,Maido
Format:	Report
Language:	English
Subjects:	BOUNDARY LAYER CONICAL BODIES DISTRIBUTION EXPERIMENTAL DATA HYPERSONIC FLOW PRESSURE SLENDER BODIES SURFACE TEMPERATURE
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creator	Hoelmer,Werner Saarlas,Maido
description	The weak interaction effect on cone surface pressures was measured and found to be in good agreement with theory. Correlation was established at a nominal Mach number of 14 with the value of the hypersonic interaction parameter, based on free-stream conditions, ranging from 4 to 20. By using an inverse approach, the cumbersome iteration method suggested by Talbot has been simplified to a one-step calculation. The results are nearly identical with Probstein's first-order theory for values of the hypersonic interaction parameter less than twenty. Computer solutions were found for 5, 10, 15, and 20 degree semivertex angle, sharp-nosed cones at free stream Mach numbers between 5 and 20 and wall to adiabatic wall temperature ratios between .1 and 1. (Author) Report on Aerothermodynamic Investigations in High Speed Flow.
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Correlation was established at a nominal Mach number of 14 with the value of the hypersonic interaction parameter, based on free-stream conditions, ranging from 4 to 20. By using an inverse approach, the cumbersome iteration method suggested by Talbot has been simplified to a one-step calculation. The results are nearly identical with Probstein's first-order theory for values of the hypersonic interaction parameter less than twenty. Computer solutions were found for 5, 10, 15, and 20 degree semivertex angle, sharp-nosed cones at free stream Mach numbers between 5 and 20 and wall to adiabatic wall temperature ratios between .1 and 1. 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Correlation was established at a nominal Mach number of 14 with the value of the hypersonic interaction parameter, based on free-stream conditions, ranging from 4 to 20. By using an inverse approach, the cumbersome iteration method suggested by Talbot has been simplified to a one-step calculation. The results are nearly identical with Probstein's first-order theory for values of the hypersonic interaction parameter less than twenty. Computer solutions were found for 5, 10, 15, and 20 degree semivertex angle, sharp-nosed cones at free stream Mach numbers between 5 and 20 and wall to adiabatic wall temperature ratios between .1 and 1. 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subjects	BOUNDARY LAYER CONICAL BODIES DISTRIBUTION EXPERIMENTAL DATA HYPERSONIC FLOW PRESSURE SLENDER BODIES SURFACE TEMPERATURE
title	THE WEAK INTERACTION THEORY FOR HYPERSONIC FLOW OVER CONES
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