Airfoil seсtion in the near-sonic flow of gas

Авіаційно-космічна техніка та технологія

Дмитрий Юрьевич Жиряков¹  Юрий Александрович Крашаница¹ 

[1] Национальный аэрокосмический университет им. Н. Е. Жуковского «Харьковский авиационный институт», Харьков;

关键词: летательный аппарат;    аэродинамический профиль;    трансзвуковое обтекание;    скачек уплотнения;    ударная волна;    численные методы;    число маха;    невозмущенный поток;    аэродинамические характеристики;    центр давление;   

DOI  :  10.32620/aktt.2021.2.03

来源: DOAJ

【 摘 要 】

The subject of investigation in this article is transonic flow. This is a condition in which local speeds of sound are appears on the wing surface, even at the subsonic speed of the nonturbulent flow. As a result, at a certain speed of the incoming flow, the flow regime around the aerodynamic surface will change sharply, which in turn changes the aerodynamic characteristics. Aerodynamic surfaces of the most transport category airplane experience transonic airflow during flight. The goal of the investigation is to study aerodynamic characteristics using numerical methods. The use of numerical methods in the design of aircraft structures is used more and more often to determine the optimal parameters for given operating conditions. This contributes to obtaining a more optimal and perfect design. In this article, we carried out a numerical analysis of the aerodynamic characteristics of airfoils in the transonic flow case using the CAE system CFD ANSYS. As a result of the research, the distributions of the pressure coefficients over the profile surface were obtained. The nature of the flow is obtained, which is similar to the picture of the pressure coefficients for transonic flow in the published sources of this topic. In the area of the middle of the profile, a shock-wave is observed. As a result, the flow around the airfoil changes, which contributes to a change in aerodynamic characteristics. The behavior of the aerodynamic drag and lift coefficients depending on the speed of the Mach number is considered. Also, the position of the center of pressure was analyzed at various velocities of the nonturbulent flow. The calculation was carried out at the cruising altitude of a medium-range aircraft of 11 km. For the calculations, we used the characteristics of the air temperature, the pressure of a given height from the table of the standard atmosphere.

【 授权许可】

Unknown