Abstract
A numerical method for the calculation of the nonlinear aerodynamic characteristics of wing-body configurations in steady low subsonic flow has been developed. The method is based on a combination of the linear source-panel method for the body and the nonlinear vortex-lattice method for the lifting surfaces and their separated wakes. Special emphasis is given to the understanding of the behavior and the computational accuracy of the numerical method. In order to demonstrate the capabilities of the present method, total and distributed loads are computed and compared with available experimental results. The computed examples cover simple configurations as well as more complicated geometries with greater relevance to modern missiles and aircraft. Details of the calculations clarify the significant nonlinear contribution of the body to the aerodynamic properties of the configuration. Good agreement was found between the computations and the experiments.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
