A modern nonlinear-lifting-line-theory algorithm allowing the prediction of aerodynamic coefficients and lifting-surface-pressure distribution for multiple aircraft configurations is presented. The algorithm is applied to isolated wing, high-lift systems (slat/main/flap), and multisurface configurations, with emphasis on the treatment of high-lift geometry representations. The fuselage is not geometrically modeled, but its influence is appropriately taken into account for the aerodynamic-coefficient evaluation. The results show good agreements with wind-tunnel and/or high-fidelity numerical data for the prediction of the maximum lift coefficient and the poststall behavior in subsonic and transonic conditions. The use of sectional airfoil data obtained via solutions of the Reynolds-averaged Navier–Stokes equations with infinite-swept-wing assumptions—so-called 2.5-dimensional model—is shown to greatly improve the results over traditional two-dimensional solutions.
Preliminary-Design Aerodynamic Model for Complex Configurations Using Lifting-Line Coupling Algorithm
Journal of Aircraft ; 53 , 4 ; 1145-1159
2016-07-01
Article (Journal)
Electronic Resource
English
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