Separated transonic interaction characterstics of an afterbody configuration in presence of a central propulsive jet

Mathur, NB and Sreekanth, AK (1988) Separated transonic interaction characterstics of an afterbody configuration in presence of a central propulsive jet. Technical Report. National Aeronautical Laboratory, Bangalore,India.

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    Abstract

    Experimental investigations were carried out in 0.3m13; trisonic wind tunnel at NAL to study separated transonic13; interaction characteristics of an axisymmetric afterbody13; configuration. The model chosen for these studies was an13; equivalent body of revolution of a representative combat aircraft configuration. Experiments were conducted in the the free stream Mach number range of 0.98 to 1.21 at constant Reynolds number of 35xlo6/m keeping model at zero degree of incidence. Jet pressure ratio was varied from 1 to about 6. The jet at nozzle exit was sonic throughout these tests.With the availability of the experimental data in the transonic Mach number range, an attempt has been made to predjct the location of the separated flow region over the afterbody without and with the presence of a propulsive jet. Available experimental results for the jet-off, simulated sting and separation locations predicted from modified Page's and Reshotko-Tucker's separation criterion compared well with the present results for the jet-off condition.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Afterbody nozzle flow;Transonic turbulent shock-boundary layer;Interaction separation oil flow
    Subjects: ENGINEERING > Fluid Mechanics and Thermodynamics
    Division/Department: Fluid Dynamics, Fluid Dynamics
    Depositing User: M/S ICAST NAL
    Date Deposited: 03 Nov 2006
    Last Modified: 24 May 2010 09:52
    URI: http://nal-ir.nal.res.in/id/eprint/3182

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