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Proceedings Paper

Design and performance predictions of smart wing for transonic cruise
Author(s): Fred Austin; William C. Van Nostrand; Michael J. Siclari; Paul Aidala; Robert Clifford
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Paper 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.

Paper Details

Date Published: 1 May 1996
PDF: 9 pages
Proc. SPIE 2721, Smart Structures and Materials 1996: Industrial and Commercial Applications of Smart Structures Technologies, (1 May 1996); doi: 10.1117/12.239132
Show Author Affiliations
Fred Austin, Northrop Grumman Corp. (United States)
William C. Van Nostrand, Northrop Grumman Corp. (United States)
Michael J. Siclari, Northrop Grumman Corp. (United States)
Paul Aidala, Northrop Grumman Corp. (United States)
Robert Clifford, ETREMA Products, Inc. (United States)

Published in SPIE Proceedings Vol. 2721:
Smart Structures and Materials 1996: Industrial and Commercial Applications of Smart Structures Technologies
C. Robert Crowe, Editor(s)

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