Conically cambered delta wings in supersonic flow. I - Basic solutions

Bera, Rajendra K and Ramachandra, SM (1979) Conically cambered delta wings in supersonic flow. I - Basic solutions. Journal of Aeronautical Society of India, 29 (3, 4). pp. 87-94.

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    Abstract

    The analysis of a conically cambered delta wing with subsonic leading edges in a supersonic stream is presented. The twist distribution chosen is a polynomial of even ordered terms in the conical coordinate for which a closed form series solution is obtained. It is found that the mean camber shapes are geometrically simple and appear to be promising in terms of low drag. To avoid flow separation at the leading edges at the design condition, the attachment line is prescribed which results in a leading edge droop for all basic shapes.

    Item Type: Journal Article
    Uncontrolled Keywords: Cambering;Delta wings;Supersonic aircraft;Cambered wings;Exact solutions; Aeronautics;Geometry;Drag (hindrance);Mathematical analysis;Separation;Accessories; Camber;Subsonic aircraft;Supersonic flow;Design engineering;Streams;Aerodynamic characteristics;Cambered wings;Delta wings
    Subjects: AERONAUTICS > Aircraft Design, Testing & Performance
    AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics, Other
    Depositing User: Ms. Alphones Mary
    Date Deposited: 04 May 2006
    Last Modified: 24 May 2010 09:40
    URI: http://nal-ir.nal.res.in/id/eprint/1195

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