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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

Report Number: FDL TDR 64-10
Author: Meckler, Lawrence
Corporate Author: Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1963-09
Pages: 146
Contract: AF33(616)-8130
Project: 8219
Task: 821902
AD Number: AD0608304

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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