Computation of HyShot scramjet flows in the T4 experiments

Michiko Furudate*, Bok Jik Lee, In Seuck Jeung

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

4 Scopus citations

Abstract

Numerical simulations of the HyShot scramjet flows in the T4 shock tunnel experiments are carried out. In order to realistically determine the freestream conditions in the test section, the nozzle flow is calculated by a thermochemical nonequilibrium axisymmetric flow solver. Using the obtained freestream conditions, a flow for the HyShot scramjet model is calculated. The results are compared with the experimental data and the CFD calculated results using the nominal freestream conditions, which are deduced under the thermal equilibrium assumption.

Original languageEnglish (US)
Title of host publicationA Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
Pages1419-1428
Number of pages10
Volume2
StatePublished - 2005
Externally publishedYes
Event13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference - Capua, Italy
Duration: May 16 2005May 20 2005

Other

Other13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
CountryItaly
CityCapua
Period05/16/0505/20/05

ASJC Scopus subject areas

  • Engineering(all)

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