Performance of GTX- 35 VS Engine Scaled Nozzles

Chidananda, MS and Jaganatha Rao, B and Venkatesh, S and Krishna Kumar, VS and Davis, A (1995) Performance of GTX- 35 VS Engine Scaled Nozzles. Project Report. National Aerospace Laboratories, Bangalore.

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    Scaled models of the GTX-35 VS engine convergent nozzles were tested under simulated . conditions with particular reference to nozzle discharge and thrust coefficients . Nozzles having half angles of 7 ° , 12 ° , 22°, 30° and 35 ° were tested at pressure ratios varying upto 10 . Reynolds numbers at inlet to the test nozzles were of same order as those found in the engine . The results obtained were in broad agreement with the data available in literature and were found to be satisfactory.

    Item Type: Proj.Doc/Technical Report (Project Report)
    Uncontrolled Keywords: Propulsive nozzle; Nozzle thrust, discharge coefficient, thrust coefficient
    Subjects: AERONAUTICS > Aircraft Propulsion and Power
    Division/Department: Propulsion Division, Propulsion Division, Propulsion Division, Propulsion Division, Other
    Depositing User: Ms Indrani V
    Date Deposited: 15 Nov 2012 11:13
    Last Modified: 15 Nov 2012 11:13

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