Abstract
A flight-test technique has been developed under NASA Dryden sponsorship to define the aerodynamic effect of thrust level on aircraft lift and drag characteristics. Conventional stabilized speed tests require the thrust to be adjusted for each test condition and, as a result, the effect of thrust on aerodynamic characteristics cannot be easily identified. The technique utilizes quasi-steady-state maneuvers at selected power settings throughout the Mach range of the aircraft to define lift and drag coefficient variation as a function of angle of attack, Mach number, and power setting. A 20-h verification flight-test program was accomplished using a Learjet Model 35 aircraft. Significant power effects were identified which should be anticipated on any aircraft with jet engines mounted on the aft fuselage above the inboard wing section.
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