This paper lays out a comprehensive methodology for computing a low-speed, high-lift polar, without requiring additional details about the aircraft design beyond what is typically available at the conceptual design stage. Introducing low-order, physics-based aerodynamic analyses allows the methodology to be more applicable to unconventional aircraft concepts than traditional, fully-empirical methods. The methodology uses empirical relationships for flap lift effectiveness, chord extension, drag-coefficient increment and maximum lift coefficient of various types of flap systems as a function of flap deflection, and combines these increments with the characteristics of the unflapped airfoils. Once the aerodynamic characteristics of the flapped sections are known, a vortex-lattice analysis calculates the three-dimensional lift, drag and moment coefficients of the whole aircraft configuration. This paper details the results of two validation cases: a supercritical airfoil model with several types of flaps; and a 12-foot, full-span aircraft model with slats and double-slotted flaps.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Semi-Empirical Prediction of Aircraft Low-Speed Aerodynamic Characteristics


    Contributors:

    Conference:

    Science and Technology Forum (SciTech 2015) ; 2015 ; Kissimmee, FL, United States


    Publication date :

    2015-01-05


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English