ANALYSIS OF A FOLLOW-ON LOW SPEED WIND TUNNEL TEST OF A HIGH MASS RATE VECTORED PROPULSION FLOW MODEL.
LING-TEMCO-VOUGHT INC DALLAS TEX LTV VOUGHT AERONAUTICS DIV
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An analysis of data obtained from a second, 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 exhausts on the wing trailing edge flap and out of the lower surface of the wing. The exhaust flows can be independently vectored through 90 degrees. Force and moment data are presented with and without a simulated, stationary ground plane in place. Pressure data in the form of spanwise and chordwise pressure distributions are given for the wing and horizontal tail. Flow angularity measurements at the location of the horizontal tail are shown. The results of this analysis show that 1 The maximum thrust removed lift coefficient for this wing is 2.7. 2 Jet flap type pressure distributions are obtained on the wing. 3 There is no noticeable change in wing pressure distribution due to the presence of the horizontal tail. 4 There is a 7.7 percent reduction in static thrust due to the presence of the ground board. 5 A significant variation in the flow field in the vicinity of the tail results from the different wing configurations. Author