Pressure and Heat Transfer Measurements at Mach 13 and 19 for Flows Ahead of Ramps, Over Expansion Corners, and Past Fin-Plate Combinations: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

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Report Number: FDL TDR 64-144
Author(s): Hatofilis, Stavros A.
Corporate Author(s): Grumman Aircraft Engineering Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-09
Pages: 56
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
Identifier: AD0608040

This report presents heat transfer and pressure distributions for hypersonic flows ahead of ramps, over expansion corners, and past fin-plate combinations. Two basic models were used for these experiments: 1) a flat plate with a full span ramp (trailing-edge flap) on one surface and an expansion corner on the other, and 2) a flat plate with wedge shaped fins mounted on the upper surface and an expansion corner on the lower surface. Both sharp leading edge models were tested in the Grumman Hypersonic Shock Tunnel at Mach 13 and 19. The plate-flap model was tested at angle of attack = -15 to +30 degrees, with flap deflections from 0 to 45 degrees, at Reynolds numbers per foot of 0.8 x 100000 to 1.4 x 100000 at Mach 19 and of 1.2 x 100000 at Mach 13. The fin- plate model was tested at angle of attack = 0 only, with 15 degree wedge shaped fins having two different heights at a Reynolds number per foot of 2.4 x 100000 at Mach 13 and of 0.8 x 100000 at Mach 19.

Provenance: Lockheed Martin Missiles & Fire Control

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