#RC WING AIRFOIL GENERATOR SOFTWARE CODE#

Xfoil, developed by Mark Drela, is utilized as the airfoil analysis code in the numerous studies that are related to the design of fixed and rotary wings, wind turbine blades, and marine propellers.

To obtain accurate results in the optimization problems, the function evaluator should be a verified and widely used analytical or numerical analysis tool. In addition to satisfying the performance merits, developing a mathematical proof of the optimized aircraft at the end of the design phase is crucial.

Simultaneously, faster solutions of the optimization problems have enabled the definition of optimization problems that have objective functions and constraints defined by different disciplines to satisfy the expected performance merits of the aircraft in the conceptual design. However, at present, the design group has expanded and divided into subgroups because of the complexity of the aircraft, which is a result of the technological advances. In the early years of aviation, a small group of engineers, led by a design engineer who had experience in both design and manufacturing, were responsible for the conceptual design. Recent advances in computer technology have advanced the conceptual design of an aircraft using advanced optimization tools rather than rough sketches and calculations on paper. It is demonstrated that defining the root bending moment, the wing area, and the available power constraints in the aerodynamic optimization problems leads to more realistic wing planform and airfoil shapes. The third optimization problem is obtained by adding the level flight condition and the available power constraints at the maximum speed and the level flight condition at the minimum speed of the baseline unmanned air vehicle to the second problem. The functional constraints related to the wing weight, the wing planform area, and the root bending moment are added to the first optimization problem, and the second optimization problem is constructed. In the first problem, the maximization of is the objective function, while level flight condition at maximum is defined as a constraint. Three different optimization problems are solved. The sequential quadratic programming algorithm of the MATLAB optimization toolbox is used for the solution of the constrained optimization problems. The agreement between the results at the low and moderate angle of attack values is observed. The outcomes are compared with the results of the solver based on the nonlinear lifting-line theory implemented into XLFR5 and the transition shear stress transport model implemented into ANSYS-Fluent. The aerodynamic analysis tool developed by the coupling of the numerical nonlinear lifting-line method to Xfoil is used to obtain lift and drag coefficients of the baseline wing. In this study, the optimization of a low-speed wing with functional constraints is discussed.

Rc wing airfoil generator software