Analysis of a Low Speed Wind Tunnel Test of a High Mass Rate Vectored Propulsion Flow Model

摘要

An analysis of selected portions of the data resulting from a low speed wind tunnel test of a semi-span model of a VTOL aircraft is presented. The model features an integrated propulsion/lifting surface system as well as a horizontal tail located on an aft, wing tip extension. The propulsion system flow, simulated with cold air, exhausts over the wing trailing edge flap (flap jet) and out of the lower surface of the wing (wing box jet). The exhaust flows can be independently vectored through 90 degrees. Force and moment data are presented for both static and forward flight conditions. Some comparison with theoretical predictions are presented. Portions of the data are shown with the direct thrust components removed. The results of this analysis show that: (1) the outboard location of the horizontal tail provides a reduction in airplane induced drag, (2) a significant portion of the theoretical jet flap effect is obtained with the wing box jet directed parallel to the wing chord plane, (3) a reduced jet flap effect is available with deflections of the wing box jet away from the wing chord plane, and (4) further testing is desirable for a better understanding of the characteristics of this configuration. (Author)