Accession Number : ADA324455
Title : Flow Patterns and Heat Exchange in Supersonic Vortex.
Descriptive Note : Final rept.,
Corporate Author : TSENTRAL'NYI AERO-GIDRODINAMICHE'SKII INST MOSCOW (RUSSIA)
Personal Author(s) : Borovoy, V. Ya.
PDF Url : ADA324455
Report Date : 1994
Pagination or Media Count : 204
Abstract : In many cases vortices are being generated on the aircraft surface: on the upper wing and body surfaces, in the vicinity of the deflected fins. They can essentially influence pressure distribution and heat transfer. The vortex generated on the upper surface of a body or a wing can encounter the shock wave in front of the fin, located downstream. Another example is: interaction of the vortex, generated by a canard, a strake or a nose flap intended for aircraft trimming with the wing or fin shock wave. A case important for practical purposes is described in: interaction between the vortex and inlet shock waves qualitatively changes the inlet entry flow pattern. A similar phenomenon can be observed in the case of interaction of the vortex generated in the inlet with the pylon of the air breathing jet combustion chamber. In this context, it is worthwhile to investigate the vortex structure and its interaction with the streamlined body.
Descriptors : *VORTICES, *FLOW VISUALIZATION, *SUPERSONIC FLOW, HEAT TRANSFER, SHOCK WAVES, FLOW FIELDS, WIND TUNNEL TESTS, FLAPS(CONTROL SURFACES), SUPERSONIC COMBUSTION, HEAT FLUX, SUPERSONIC CHARACTERISTICS, PRESSURE DISTRIBUTION, INCOMPRESSIBLE FLOW, STRAKES, SUPERSONIC WIND TUNNELS, FINS, AIRCRAFT NOSES, CANARD CONFIGURATIONS, TRIM(AERODYNAMICS).
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE