WIND-TUNNEL INVESTIGATION OF THE HOVERING, TRANSITION, AND CRUISING PERFORMANCE OF AN ARRESTED ROTOR (TRIDENT) VTOL AIRCRAFT CONCEPT.
DAVID TAYLOR MODEL BASIN WASHINGTON D C AERODYNAMICS LAB
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Wind-tunnel tests were conducted to evaluate static stability and control characteristics with emphasis on determining the magnitude of transition problems. Evaluating the compatibility of the competing internal and external aerodynamic requirements for high static lift and efficient cruising was an additional test objective. Test results show that the model exhibits a strong directional trim shift through transition. The pattern selected for rotor arrestment during evaluation of the transition characteristics was not acceptable on the basis of power required to support vehicle weight or control of trajectory. The results further indicated that the performance potential of the ducted rotor -nozzle system may be limited because of the structural requirements. Model rotor duct design, from the standpoint of internal aerodynamics, was compromised by adding structure to accommodate the wing bending loads for high-speed cruising. Author