Cold jet simulation RIG for the NAL 1.2M trisonic wind tunnel

Mathur, NB and Mohan, Jai and Lokhandawala, OA (1978) Cold jet simulation RIG for the NAL 1.2M trisonic wind tunnel. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    Abstract

    This report describesa jet simulationrig designed for testing aftbodies of certain aerodynamic vehicles in the supersonictest section lt;;:gt;xA3;1. 2m trisonicwind tunnel. An aftbody model is mounted on-the side wall of the wind tunnel with the help of an unswept tapered strut. tir at a pressure of lO.55kg/cms2 is supplied to the model through a 15Omm' diameter pipe and a duct in the strut. This rig can be used for testing axisymmetric b?at tailed or flared aftbod with a convergent or convrgent-divergent nozzle. L 304.8mm Schlieren glass window is provided for the visualization of the flow field near the nozzle exit plane. The rig is primarily designed for Schlieren flow visualization and pressure measurements. The rig was succes$fully used for testing of a flared aftbody at a free stream Mach number of 3.7 and a jet Mach number of 3.72.13; The report also discusses jet and air frame interference effects the nature of the aftbody flow field and cold jet simulation.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Flow field;Jet simulation;Transition piece
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics, Aerodynamics, Aerodynamics
    Depositing User: Deputy Head Poornima Narayana
    Date Deposited: 22 Aug 2006
    Last Modified: 24 May 2010 09:49
    URI: http://nal-ir.nal.res.in/id/eprint/2562

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