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.
Semi-Empirical Prediction of Aircraft Low-Speed Aerodynamic Characteristics
Science and Technology Forum (SciTech 2015) ; 2015 ; Kissimmee, FL, United States
2015-01-05
Conference paper
No indication
English
Semi-Empirical Prediction of Aircraft Low-Speed Aerodynamic Characteristics (AIAA 2015-1679)
British Library Conference Proceedings | 2015
|Prediction methods for aircraft aerodynamic characteristics
TIBKAT | 1974
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