This thesis presents the development of a numerical software for calculating static aerolastic responses of elliptical airplane wings. Classic computational methods treat structural and aerodynamic loads independently, while modern approaches utilize FEM and CFD analyses, which are significantly slower. Our code offers a solution that quickly provides a good approximation of the real-world loading conditions on the airplane wing. The theory is based on the Euler-Bernoulli beam model, and the nonlinear model of torsional twists of elliptical shell with a variable cross-section and load. The program requires polars of airfoils obtained from either simulations or tests. Numerical model was developed in Wolfram Mathematica,
the results were verified using Ansys. Analysis shows a strong impact of torsional twists on the lift distribution at high speeds, while the impact of aerolastic effects is smaller, though non-negligible.
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