An Aerodynamic Profiled Aircraft Algorithm

The neeed for a computer program for performing rapid and accurate evaluation of the aerodynamic characteristics of an aircraft is evident during evaluation of a preliminary design configuration when both time and geometry definition are limited. Transonic similarity theory, Sinnott airfoil theory, Polamus equation and DATCOM method are applied. The theories and calculating process based on parts combination empirical methods were elaborately discussed, which were used to calculate the aerodynamic characteristics of irregular body section wing-body-tail combinations. Basing on these methods, author has developed the computation program. Two calculation examples are used in this thesis, they are C-141A plane model and a dispenser model. The aerodynamic coefficients results of the calculation were coherent with the result of the wind tunnel experiments. In end, the results was analyzed and compared with experimental results to evaluate the program' s application value and limitation. This set of methods are suitable for the calculation of the irregular body section aircrafts.