Abstract
A low-speed wind tunnel test was conducted to further develop a propulsive lift concept applicable for use in advanced fighter aircraft with short takeoff and landing requirements. The Transverse Thrust Lift Augmentation (TEA) concept operates by diverting a large proportion of the engine exhaust in a lateral (transverse) direction behind the deflected trailing edge flaps and increasing wing lift through super-circulation. Pitch thrust vectoring of the remaining axial exhaust is used for trim and control. The existing TTLA aeropropulsion test data base obtained through wind tunnel testing in prior years was limited to one particular wing planform a clipped delta wing of aspect ratio 2.1. The current test explores the effectiveness of =LA on various wing planforms. A total of eight wing planforms were tested on a simple wing body model. Data on the effects of wing aspect ratio, wing trailing edge sweep, and taper ratio on TTLA lift augmentation were obtained. The model utilized two sets of nozzles of different sizes designed to simulate two main engine airflow diversion fractions. Testing to establish the roll control effectiveness of spoilers operating with TTLA was also performed.
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