On the representation of the drag polar of a fighter aircraft

Yajnik, KS and Subbaiah, MV (1975) On the representation of the drag polar of a fighter aircraft. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    The values of lift coefficient encountered during manoeuvres13; of a fighter aircraft are known to be wel1 beyond the range where the classical representation CD = CDo + k ci is a good approximation. Examination of available test data on several configurations showed that the drag polars can be approximately represented as CD = CDo + k ci + a C with a suitable choice of a and n.13; A simpler representation with the value of n equal to 413; was carefully tested against detailed test data on two configurations for Mach numbers ranging from 0.5 to 1.5 and angles of attack from -4xB0; to 20xB0;. Agreement was generally better than 5% in transonic and supersonic range. The agreement was satisfactory in the subsonic range, although the departures were occasionally larger in magnitude. It is suggested that the representation with n = 4 can be advantageously used in the turn calculations of fighter aircrafts.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Manoeuvres;Drag polars;Subsonic range
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics, Aerodynamics
    Depositing User: M/S ICAST NAL
    Date Deposited: 14 Nov 2006
    Last Modified: 24 May 2010 09:49
    URI: http://nal-ir.nal.res.in/id/eprint/2580

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