Supercritical wing design for combat aircraft

Nandanan, M and Ramaswamy, MA (1985) Supercritical wing design for combat aircraft. Technical Report. National Aeronautical Laboratory, Bangalore, India.

Full text available as:
[img] PDF
Restricted to Archive staff only

Download (4Mb)


    This paper deals with the use of lifting symmetric super-13; critical airfoils in the wing design of a combat aircraft.13; For transonic combat aircraft requiring supersonic accele-13; ration, the usual supercritical airfoil which invariably has : camber is not suitable because of the supersonic wave drag penalty arising from the camber. TherexA3;ore, 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 demonstrate that the benefits obtained in the two dimensional performance extends to some extent even for the three-dimensional performance when such symmetric supercritical airfoils are used in finite wings of the combat type aircrafts.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Supercritical wing design;Combat aircraft;Three-dimensional performance;Symmetric supercritical airfoil;13; Design and off-design performance;Fictitious gas method
    Subjects: AERONAUTICS > Aircraft Design, Testing & Performance
    AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics, Aerodynamics
    Depositing User: M/S ICAST NAL
    Date Deposited: 29 Aug 2006
    Last Modified: 24 May 2010 09:49

    Actions (login required)

    View Item