Wind tunnel tests on LCA 6.02 configuration

Narayan, KY and Gopinath, N and Seshagiri, SN (1988) Wind tunnel tests on LCA 6.02 configuration. Project Report. National Aerospace Laboratories, Bangalore.


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    Tests were conducted in the NAL 1.2m trisonic wind tunnel on a 1/20th scale model of the LCA Stage 6.02 configuration. The tests were carried out in a Mach number range of 0.5 to 1.6 and over an angle of attack range which varied from -5 deg to +28 deg at M = 0.5 to -5 deg to +12 deg at M = 1.6. The test Reynolds number (based on wing mean aerodynamic chord) varied between 4.8 to 10.28 millions depending on the Mach number. The tests Included : (i) determination of the longitudinal characteristics of the configuration and (ii) determination of longitudinal, lateral and directional control powers.

    Item Type: Proj.Doc/Technical Report (Project Report)
    Uncontrolled Keywords: LCA;High speed tests
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics, Aerodynamics , Aerodynamics
    Depositing User: Smt Bhagya Rekha KA
    Date Deposited: 03 Sep 2012 13:40
    Last Modified: 25 Sep 2012 10:00

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