INVESTIGATION OF DISTRIBUTION OF PRESSURE ON SOME STAR-SHAPED BODIES AT MACH APPROX. = 4

The results of an experimental investigation of pressure distribution on star-like bodies in supersonic flows in an aerodynamic wind tunnel at M = 3.85 plus or minus 0.1 and Re = 6,000,000 are presented. The models, experimental setup, and measuring techniques are described in detail. Pressure measu...

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Bibliographic Details
Main Authors: Gonor,A. L, Shvets,A. I
Format: Report
Language:English
Subjects:
AERODYNAMIC CONFIGURATIONS
Aerodynamics
ANGLE OF ATTACK
BOUNDARY LAYER
CONICAL BODIES
DISTRIBUTION
DRAG
Fluid Mechanics
PRESSURE
REYNOLDS NUMBER
SHOCK WAVES
STAR SHAPED BODIES
SUPERSONIC CHARACTERISTICS
TRANSLATIONS
USSR
WIND TUNNEL MODELS
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Summary:The results of an experimental investigation of pressure distribution on star-like bodies in supersonic flows in an aerodynamic wind tunnel at M = 3.85 plus or minus 0.1 and Re = 6,000,000 are presented. The models, experimental setup, and measuring techniques are described in detail. Pressure measurements were obtained by manometers with tetrabromoethane liquid (gravity = 2.96 g/cm cc). The boundary layer effect upon the flow structure for various angles between wings is investigated and shock wave structures for various angles of attack (from 5 to 15 deg) are analyzed. A comparison of the experimental results with the exact theoretical data obtained previously by the author shows good agreement for all models. The ratios between the wave drags of equivalent circular cones and wave drags of models calculated from experimental data indicate that in certain cases predicted by theory the wave drag is reduced several times. (Author) Edited trans. of Zhurnal Prikladnoi Mekhaniki i Tekhnicheskoi Fiziki (USSR) n6 p122-125 1965, by E. Harter.