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Accession Number:
AD1096601
Title:
Effects of Wall Temperature in High Enthalpy Rarefied Hypersonic Separated Flow
Descriptive Note:
Technical Report,24 Jun 2016,23 Jun 2018
Corporate Author:
University of New South Wales Kensington Australia
Report Date:
2019-10-10
Pagination or Media Count:
27.0
Abstract:
The initial goals of the project were to investigate the behavior of high to moderate enthalpy rarefied hypersonic flow in a strong thermal non-equilibrium for wall temperature conditions of 300K and 1500K. Due to complexity, the highest wall temperature used was 800K. Nonetheless, this research represents, for the first time, shock tunnel experiments on a large separated hypersonic rarefied flow with a heated wall up to 800K that yielded a wall to stagnation temperature of ratio of 0.25. The experimental surface of the model was made of graphite and the experiments were conducted on a large separated flow at hypersonic conditions in free-piston driven shock tunnel at an enthalpy of 3.1 MJkg, Reynolds number of 1.34 x 106 m-1 and a Mach number of 10. Analysis and simulations, both Navier-Stokes and DSMC have shown that both primary and secondary separations are strongly influenced by the wall temperature. The results of the experiments showed reasonable agreement with numerical data and provided confidence that future work with higher temperatures is feasible using a simpler configuration. Higher temperature experiments can provide important data for modeling and design of space vehicles.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE
