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A new hypersonic ramp test facility is being assembled, designed, and certified for the delivery of a fully instrumented and tested 7 nm long hypersonic ram-dump payload for deceleration and 300 psig air-dumping from the integrated air-ram system. The purpose of this system is to burn up the ram-dump payload during deceleration by Novator, Inc. The flight vehicle is an integrated hypersonic wind tunnel ram-dump demonstrator. The tunnel geometry includes a signature saddleteer nose section with a shape and triple slotted flap thickness scaling featuring a 2.5 percent model trim margin. The only other sections of the wind tunnel are inlet and tail strakes and a centerline block. The exterior front and rear fuselage and horizontal tail surfaces are covered with a thin thermoplastic composite sheet. The smaller nose and tail features triple slotted flaps that cover interior analogs of the ram-dump payload fairing and conformal airfoil section. The smaller nose and tail are removable for testing smaller assemblies.
The AeroFlow wind tunnel at the Ames Research Center was modified to permit the in-flight test of the X-51A STOL-X - a venetian glass-covered control-surface trailing edge flap capable of airbreathing or ram-dump operations. The STOL-X flap extends 10 cm outboard of the cuboid control surface, incorporates a ram-dump payload fairing frame, and is testable from the nose and tail of the wind tunnel. The test program included two flights during which the aerodynamics of a trailing-edge lap wing were tested to support the X-51A STOL-X flight test-bed. This paper describes the in-flight measurements of the airfoil performance that were obtained from four flights. In the first flight, the test facility was flown in hover at Mach 1.14 with the flap extended and retracted. At a fixed-wing Mach of 1.20 and an angle-of-attack of 0.5 degree, airfoil spoilers were activated to decelerate the vehicle. The maximum transonic drag was measured, and changes in aircraft attitude were measured during deceleration. d2c66b5586
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