Wind tunnel tests on MiG-2114 aircraft model with combat flaps

Narayan, KY and Gopinath, N and Seshadri, SN (1985) Wind tunnel tests on MiG-2114 aircraft model with combat flaps. Project Report. NAL, Bangalore.

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    Abstract

    Tests have been conducted in the NAL 1 .2m tunnel on a 1/17th scale model of the MiG_21M aircraft to study the effectiveness of trailing edge flaps as manoeuvre enhancing devices, Tests were conducted at Mach numbers of 0, 5, 0 .7 and 0.9 . Schedules for deflection of flap and horizontal tail to give maximum trimmed L/D as a function of trimmed angle of attack are presented for the three Mach numbers and at two levels of static stability. The results indicate that increments of the Order of 10% in trimmed lift at angles of attack of about 12 degrees are achievable through the use of appropriately scheduled flap and horizontal tail deflections.

    Item Type: Proj.Doc/Technical Report (Project Report)
    Uncontrolled Keywords: MiG-21;Combat flaps
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics, National Trisonic Aerodynamic Facility, Aerodynamics
    Depositing User: Mr Nisanth
    Date Deposited: 09 Jul 2012 16:10
    Last Modified: 09 Jul 2012 16:10
    URI: http://nal-ir.nal.res.in/id/eprint/10549

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