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
Item
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Title
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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
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Date
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1964
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Index Abstract
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Coming Soon
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Photo Quality
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Complete
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Report Number
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FDL TDR 64-142
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Corporate Author
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Grumman Aircraft Engineering Corporation
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Extent
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438
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Identifier
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AD0608830
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Access Rights
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OTS
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Distribution Classification
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1
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Contract
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AF 33(616)-8130
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DoD Project
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8219
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DoD Task
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821902
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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None
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Abstract
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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.
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Report Availability
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Full text available
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Date Issued
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1964-09
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Laboratory
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AF Flight Dynamics Laboratory
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Provenance
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Lockheed Martin Missiles & Fire Control
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AFRL/VACA
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Type
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report
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Format
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1 online resource
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Creator
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Meckler, Lawrence