Aerodynamic heating in three-dimensional shock wave turbulent boundary layer interaction induced by sweptback sharp fins in hypersonic flows

Shigeru Aso, Shouzo Maekawa, Masanori Hayashi

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

For the fundamental study of aerodynamic heating of winged vehicle and space planes in hypersonic flow the detailed structure of three-dimensional shock wave/turbulent boundary layer interaction region induced by sweptback sharp fins are investigated carefully by oil flow technique and pressure distribution. The major objectives of the present study are to study the effects of the shape of the leading edge of the fin to the flow fields on the body and to study the effect of the sweep angle of the leading edge of the fin to the interaction region. Also aerodynamic heating phenomena in the flow fields are investigated by using a new technique. For the measurements a new method of measuring heat flux developed by the present authors are used. The new method is based on a new type of thin-film heat transfer gauge with high spatial resolution and fast response. The results suggest the effects of the shape of the leading edge to the flow fields are quite significant and the sweep of the leading edge of the fin to freestream is quite important to reduce the interaction region.

Original languageEnglish
Title of host publicationProceedings - Society of Automotive Engineers
PublisherPubl by SAE
Pages591-598
Number of pages8
EditionP-246
ISBN (Print)1560911468
Publication statusPublished - 1991
EventInternational Pacific Air and Space Technology Conference and 29th Aircraft Symposium Proceedings - Gifu, Jpn
Duration: Oct 7 1991Oct 11 1991

Other

OtherInternational Pacific Air and Space Technology Conference and 29th Aircraft Symposium Proceedings
CityGifu, Jpn
Period10/7/9110/11/91

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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