The Technique of Optimizing the Length of the Front Section of a Bicalibre Aircraft with a Detachable Propulsion System According to Criteria of Ballistic Efficiency
摘要
Abstract
A method is proposed for selecting the optimal length of the front section of a bicalibre aircraft according to the criterion of maximum range, using which a parametric study of the influence of geometric and mass parameters on the size ratio of the aircraft is carried out.