Drag divergence Mach number for NCAD-21463 Wing with 20 leading edge sweep angle

Singh, Manish K and Dhanalakshmi, K and Meenakshi, and Mathur, JS (2011) Drag divergence Mach number for NCAD-21463 Wing with 20 leading edge sweep angle. Project Report. CSIR-NAL, Bangalore.

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    Abstract

    CSIR-NAL has started preliminary work on design of 70- 90-seater civilian aircraft that is suitable for Indian conditions and can operate from airports having minimum infrastructure facilities. This aircraft should be at least on par with the aircraft presently available in market in terms of efficiency, speed and quietness to remain competitive. NCAD (National Civil Aircraft Development) design team has designed such a wing suited for turbofan version. Drag divergence Mach number plays a major role to decide the maximum operating speed without a severe drag penalty. The in-house developed CFD Euler code JUEL3D has been used to compute the drag divergence Mach number for NCAD-21463 wing with 20 leading edge sweep back angle for lift coefficient of 0.4, 0.5 and 0.6. The drag divergence Mach number is found to be 0.74, 0.72 and 0.70 respectively for lift coefficient of 0.4, 0.5 and 0.6.

    Item Type: Proj.Doc/Technical Report (Project Report)
    Subjects: AERONAUTICS > Aerodynamics
    AERONAUTICS > Aircraft Design, Testing & Performance
    Division/Department: Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division
    Depositing User: Mr Manish K. Singh
    Date Deposited: 22 Feb 2011 10:08
    Last Modified: 22 Feb 2011 10:08
    URI: http://nal-ir.nal.res.in/id/eprint/9153

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