Nandanan, M and Ramaswamy, MA (1987) Lifting symmetric supercritical airfoils for wing design of combat aircraft 13; 13;. Communications in Applied Numerical Methods, Vol. 3 . pp. 463-468. ISSN 0748-8025Full text not available from this repository.
This paper deals with the use of lifting symmetric supercritical airfoils in the wing design of a combat aircraft. For transonic combat aircraft requiring supersonic acceleration, the usual supercritical airfoil which invariably has camber is not suitable because of the supersonic wave drag penalty arising from the camber. Therefore, lifting symmetric supercritical airfoils which overcome this disadvantage were developed by the authors, and their beneficial effects in the two-dimensional case were demonstrated earlier. The objective of this paper is to illustrate that, even when an unsophisticated approach is used for adopting such a lifting symmetric supercritical airfoil to the wing of a particular combat aircraft configuration, the theoretical analysis indicates some benefits. It is therefore felt that the use of lifting symmetric supercritical airfoils in the design of wings of combat aircraft usiing more sophisticated design techniques may be worth considering.
|Item Type:||Journal Article|
|Additional Information:||Copyright for this article belongs to John Wiley amp; Sons, Ltd.|
|Uncontrolled Keywords:||Airfoils;Hoisting;Combat aircraft;Wings (aircraft);Design engineering;Mathematical models;Camber;Supersonic aircraft; Drag (hindrance);Waves;Aircraft design;Fighter aircraft lifting bodies;Aspect ratio pressure distribution;Symmetry|
|Subjects:||AERONAUTICS > Aerodynamics|
|Depositing User:||M/S ICAST NAL|
|Date Deposited:||13 Oct 2006|
|Last Modified:||24 May 2010 09:51|
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