841. Design and Experimental Studies of a Thrust Deflector for VTOL Direct Lift Engines
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Paper
Abstract
Design and experimental studies were conducted on a thrust deflector applicable to fuselage mounted lift engines installed in a VTOL aircraft. It was assumed that the equivalent of 60 degree (-15 degree to +45 degree) of total deflection will be required and that an aerodynamically smooth external surface is necessary for high speed forward flight. With these requirements, a two-dimensional external flap deflector, integral with the fuselage, was investigated. The flap was designed as an isentropic plug nozzle, with a hinge point slightly downstream of the throat. Massflow, shadowgraph, pressure and force data were obtained. The shadowgraph and pressure data indicated that for all positive deflections (0 to 45degree) the flow could be deflected in a very short length via a low loss shock system. For negative deflections an efficient coanda effect was obtained. The experimental data indicate that a single three-dimensional external flap deflector is an efficient device for thrust vectoring of aft engines.
