A rig for testing afterbodies of aerospace vehicles in presence of j e t in 0.3m trisonic wind tunnel

Mathur, NB and Ramakrishnan, MS (1984) A rig for testing afterbodies of aerospace vehicles in presence of j e t in 0.3m trisonic wind tunnel. Technical Report. National Aeronautical Laboratory, Bangalore,India.

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    Abstract

    This report describes a test rig designed for testing afterbody models of various aerospace vehicles in13; the free stream mach number range of 0.4 to 2.0 and jet13; pressure ratios range of 1.0 to about 10.0 in the 0.3 m13; trisonic wind tunnel. Special design features of the rig13; are (a) interchangibility for axisymmetric configurations13; and non-axisymmetric shapes of realistic aircraft configurations, (b,) easier changing of various afterbody/nozzle geometries,tunnel with the help of a hollow, unswept tapered strut.Compressed air required for jet simulation during experiments is supplied to the model at a maximum available Model i s mounted to the side wall of wind pressure of 10.55 kg/cms2 through SO m/150 m diameter pipe line and a duct in the trust, A 152 mm Schlieren glass with its frame is specially designed and is mounted such that it provides the visualization of flow field around the afterbody-nozzle exit region, The rig can also be used for the direct measurement of afterbody drag by using an internal strain gauge balance.The rig was successfully used for pressure measurements and Schlieren flow visualization studies on an axisymmetric boattailed afterbody model (which was an equivalent body of evolution of a typical fighter aircraft) in the freestream mach number range of 0.6 t o 1.1 and jet pressure ratiorange of 1.0 to 6.0, This report also discusses briefly jet and airframe interference effects and transonic flow field phenomena,13;

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Trisonic wind tunnel;Aerospace vehicles rig testing
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Flight Mechanics and Control Division, Flight Mechanics and Control Division
    Depositing User: M/S ICAST NAL
    Date Deposited: 14 Sep 2006
    Last Modified: 24 May 2010 09:50
    URI: http://nal-ir.nal.res.in/id/eprint/2729

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