Determination of aerodynamic nozzle contours for transonic cascade tunnel

Narayanamurthy, RS (1973) Determination of aerodynamic nozzle contours for transonic cascade tunnel. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    In this report a procedure suitable for obtaining the potential aerodynamio contours of a nozzle and the necessary boundary layer corrections is described. After a description of the method, the procedure for computerising the above calculations by the said method is presented.13; The method is then used to obtain the potential flow contours of the nozzle with necessary boundary layer corrections.These are contours are proposed to be used in the transonic cascade wind Tunnel.These coi1tours13; The results obtained for various test section heights and flow Mach numbers are presented.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Aerodynamic nozzle;Transonic cascade tunnel
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Propulsion Division
    Depositing User: M/S ICAST NAL
    Date Deposited: 07 Nov 2006
    Last Modified: 24 May 2010 09:53

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