Contrails
The goal of the Contrails project is to help preserve and disseminate the technical record of 20th century aerospace research, highlighting in particular the research endeavors of the Illinois Tech community.

Heat Transfer Measurements at Mach 9 on an Aerodynamically Controllable Winged Re-Entry Configuration: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

Report Number: FDL TDR 64-142
Author: Meckler, Lawrence
Corporate Author: Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1964-09
Pages: 438
Contract: AF 33(616)-8130
Project: 8219
Task: 821902
AD Number: AD0608830

Abstract:
Heat transfer data were obtained at Mach 8 for a winged re-entry configuration with several types of aerodynamic controls. The basic model consisted of a clipped delta wing with an overslung cone-cylinder body. Most of the tests were conducted with partial span trailing edge flaps. The effects of tip fins, a hemisphere-cylinder body, a full span trailing edge flap, and a full span, plugtype, trailing edge spoiler were also investigated. The partial span flap deflection were varied between = 39 degrees in an angle of attack range of =20 degrees. Selected configurations were used to examine the angle of attack ranges of -30 degrees to -50 degrees and + 30 degrees to + 50 degrees. The major portion of the program was conducted at a unit test section Reynolds number of 3.3 x 10 to the 6th power/ft with limited comparative testing being done at a unit test section Reynolds number of 1.1 x 10 to the 6th power/ft.


Provenance:
Lockheed Martin Missiles & Fire Control
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