Performance of NAL- MSNLF-136 airfoil with boundary layer tripped at 5 and 10 of the chord

Srilatha, KR and Ramamoorthy, P (1989) Performance of NAL- MSNLF-136 airfoil with boundary layer tripped at 5 and 10 of the chord. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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    Abstract

    Recently NAL has designed a natural laminar flow airfoil NAL--MSNLF-136 for use on a-genergl aviation aircraft for the design copditions M - 0.6, R - 10 x 10 and C -0.4. In order to validate this airfoil in the NA l' x 'I' tunnh , performance calculations have been carried out with 5% and 10% boundary, layer trippings. It is generally seen that while the lift co-efficients decrease the drag co-efficients increase relative to the natural flow case

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Design;Airfoil;Laminar flow;General aviation
    Subjects: AERONAUTICS > Aircraft Propulsion and Power
    Division/Department: Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division
    Depositing User: Ms Indrani V
    Date Deposited: 13 Jul 2006
    Last Modified: 24 May 2010 09:44
    URI: http://nal-ir.nal.res.in/id/eprint/1929

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