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
Technical documentary rept.
GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE NY
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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.
- Guided Missile Reentry Vehicles
- Fluid Mechanics