Modified method of determining the planning range of a universal aerodynamic container of a given mass

Abstract

In connection with the change in the glide height of the aircraft, the parameters of the atmosphere change, including the kinematic viscosity of the air, which affects the determination of the Reynolds number Re, which in turn determines the coefficient of aerodynamic drag, which is the denominator in determining the maximum aerodynamic quality maximum aerodynamic quality. Therefore, determination of the glide distance of the aircraft, where the maximum aerodynamic quality is valid only when carrying out estimation calculations and in a small range of heights.

In the case of steady gliding, the following external forces will act on a winged aircraft: the net effect of aerodynamic forces R, the force of weight G and the force of thrust P. In the case under consideration, when P=0, all these forces must be in balance. Accordingly, for a more accurate calculation of the glide range of an aircraft, it is necessary to conduct a study on the change of maximum aerodynamic quality depending on the height.

The article presents the results of scientific research on the development of a modified method of determining the glide distance in an integral form depending on the height of use of a universal aerodynamic container of a given mass (m=700 kg, 1150 kg, 1250 kg). An aerodynamic scheme and layout of a universal aerodynamic planning container for the placement of air weapons with a diameter of up to 0.4 meters is proposed. The functional dependences of the control parameters for the formation of the trajectory of the glider in the mode of maximum aerodynamic quality in the conditions of the Standard atmosphere are constructed. This approach makes it possible to more accurately determine the glide distance of aerodynamic layouts of a given mass in the operational range of heights, depending on the tasks, possible limitations of the aircraft - the carrier and the tactics of its use.