Static Aerodynamic Characteristics at Mach 5 and 8 of 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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Static Aerodynamic Characteristics at Mach 5 and 8 of 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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1963
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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 64-10
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Corporate Author
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Grumman Aircraft Engineering Corporation
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Laboratory
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AF Flight Dynamics Laboratory
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Extent
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146
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Identifier
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AD0608304
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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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AF33(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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Six-component aerodynamic data were obtained at Mach 5 and 8 for a winged re-entry configuration having aerodynamic controls. The basic model consisted of a clipped delta wing with an over-slung body. The main controls tested were a deflected apex and partial-span trailing-edge flaps. Data were also obtained on the effect of tip fins, full-span trailing-edge flap, and trailing-edge spoiler. At Mach number 5 the data were obtained over an angle of attack range from -30 degrees to +45 degrees at a unit Reynolds number of 2.26 x 10 to the 6th power. At Mach number 8 the angle of attack range was -54 degrees to +54 degrees at the same unit Reynolds number.
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Report Availability
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Full text available
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Date Issued
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1963-09
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Provenance
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Lockheed Martin Missiles & Fire Control
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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