Порівняння злітних характеристик двох типів крила для літака з можливістю короткого зльоту та посадки

Abstract

The subject of study in this article is the effect of mechanization of the trailing edge of the wing, located along 95% of the wing console, on the lift coefficient, drag coefficient, and aerodynamic quality of the wing during takeoff operation for a wing with a high curvature profile. The purpose of this study was to determine the effectiveness of using a flap along 95% of the trailing edge of the wing console for profiles with high curvature during takeoff for aircraft with short takeoff and landing capabilities. Objectives: to set the geometric characteristics of the wing, create a mathematical model of the wing for two design cases, determine the control data for the calculation, and compare the data obtained. The method for determining the efficiency is to conduct an analysis by comparing the aerodynamic characteristics of wings with the same mechanization, namely, a single-slot Fowler flap, but the flap has a different length. In the first design case, roll control is performed using an aileron that reduces the length of the flap. In the second design case, the flap is placed along 95% of the trailing edge of the wing cantilever, and roll control is performed using interceptors. The study was conducted using the PANSYM software. A key factor is that during the calculation, the structural elements responsible for roll control are not used, i.e., they are in a non-deflected position. The influence of the screen effect is not considered. The calculation is performed at angles of attack from -5° to +15°, viscosity is considered, and the number of viscosity calculation operations is 8. Conclusions. This paper presents additional studies of the influence of the flap along 95% of the wing console edge on its aerodynamic characteristics. The scientific novelty is that the efficiency of using flaps along 95% of the trailing edge of the wing for aircraft with the possibility of short takeoff and landing in the takeoff flight mode has been proved. After comparing the obtained results of the calculation of the two mathematical models, the following conclusions were drawn: the increase in lift coefficient is 30%–50% and the increase in drag coefficient is 35%–45%, but this leads to a decrease in aerodynamic quality by 11%–21%. Thus, a significant increase in the lift coefficient makes it possible to reduce the required distance for takeoff, which is important for aircraft with the capability of short takeoff and landing.