This paper presents a thermodynamical and aerodynamical analyses of the behaviour of a hypothetical lightweight combat aircraft operating on a single engine afterburning turbojet. An airframe was selected for the aircraft thus specifying the aerodynamical characteristics. Then an engine was developed to achieve the basic criteria for the fulfillment of certain predefined mission requirements such as taking off from a runway of specified length, supercruising at particular Mach number, performing high g combat turns, etc. The engine and the airframe were coupled to form a basic aircraft. The capabilities of this aircraft were reviewed thereafter at distinct stages of flight and its capability as an interceptor aircraft was analysed. After careful consideration of all the aspects of the theoretical aircraft, it was concluded that it fulfilled the numerous mandatory requirements demanded for an interceptor aircraft.


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    Title :

    Preliminary design analysis of a lightweight combat aircraft


    Contributors:
    Saha, U K (author) / Mitra, M (author) / Menon, S J (author) / John, N T (author) / Gajapathi, S S (author) / Behera, P (author)


    Publication date :

    2008-04-01


    Size :

    7 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Preliminary design analysis of a lightweight combat aircraft

    Saha, U.K. / Mitra, M. / Menon, S.J. et al. | Tema Archive | 2008



    Supersonic combat aircraft design

    FLETCHER, J. / BURNS, B. | AIAA | 1979


    Combat-ready aircraft

    Schriever, B.A. | Engineering Index Backfile | 1953