Design and performance predictions of smart wing for transonic cruise

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Abstract
The development of aircraft lifting surfaces that change shape to enable relatively shock-free performance throughout a range of design points in the transonic region is described. This type of reduced-drag airfoil can increase range, decrease fuel expenditure, increase cruising speed, increase lift, or accomplish a combination of these desirable effects. Preliminary payoff studies on a Gulfstream III aircraft with a hypothetical smart wing, show that if 1000 lbs. were added to the weight of the aircraft to incorporate smart-wing technology, and the coefficient of drag CD could be decreased by 20 counts (0.0020), 5% less fuel would be required or the range could be increased by 5% with the existing fuel. Airfoil shapes are computed with a stochastic optimization method based on simulated annealing. Drag reduction is presented as a function of flight condition, region of surface control, and number of actuators. Design and development of an experimental TERFENOL-D actuator to provide the variable airfoil shape required for optimum performance are also discussed.

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