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Investigation of the three-dimensional turbulent flow downstream of swept slot injection in hypersonic flowResults of an experimental and numerical investigation of tangential swept slot injection (sweep angles of 22.5 and 45 deg) into a thick turbulent boundary layer at Mach 6 are presented. Film cooling effectiveness, skin friction, and flow structure downstream of the swept slot injection are investigated. The data are compared to that for unswept slots, and it is found that cooling effectiveness and skin-friction reductions are not significantly affected by sweeping the slot. Predictions of cooling effectiveness and skin friction obtained by a numerical finite-difference technique agree reasonably well with experimental surface variables. As in previous supersonic two-dimensional slot research, reduced mixing was found downstream of the slot lip in the present three-dimensional case.
Document ID
19740053175
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hefner, J. N.
Cary, A. M., Jr.
Bushnell, D. M. (NASA Langley Research Center Hypersonic Vehicles Div., Hampton, Va., United States)
Date Acquired
August 7, 2013
Publication Date
July 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 74-679
ASME 74-HT-13
Meeting Information
Meeting: Thermophysics and Heat Transfer Conference
Location: Boston, MA
Start Date: July 15, 1974
End Date: July 17, 1974
Sponsors: American Society of Mechanical Engineers, American Institute of Aeronautics and Astronautics
Accession Number
74A35925
Distribution Limits
Public
Copyright
Other

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