Flow characteristics in the operational range angles of attack and Mach numbers numerical investigation of helicopter airfoils

DOI: 10.34759/trd-2023-131-13


Tarasov A. L.

Branch of the Military Training and Scientific Center of the Air Force «N.E. Zhukovsky and Y.A. Gagarin Air Force Academy» in Syzran, Marshal Zhukov str., 1, Samara region, Syzran, 446007, Russia

e-mail: andreyt4884@mail.ru


The article presents the results of calculation of distributed and integral aerodynamic characteristics of helicopter airfoils NACA0012, NACA23012, VR12 and HH02 in the operational range of changes in angles of attack and Mach numbers, obtained by numerical simulation based on RANS. Modeling of helicopter airfoils flow was carried out considering the presence of a laminar-turbulent transition in the boundary layer on their surface, the presence of disruptive phenomena and compressibility of the flow. Calculations were performed by using the ANSYS Fluent software package. The results obtained are satisfied with the data of known experimental studies. The description of the features of finite-difference mesh used for calculations, boundary and initial conditions, turbulence models, solver settings is given. The distributed aerodynamic characteristics of the airfoils are presented in the form of coordinate diagrams of the distribution of the pressure coefficient over their contours. Integral airfoils aerodynamic characteristics are presented in the form of graphical dependencies and diagrams. According to the results of the calculations, the patterns of behavior of the distributed and integral aerodynamic characteristics of the studied airfoils are revealed when the flow conditions change in the entire possible operational range of operation. The comparison and comparative analysis of the studied airfoils characteristics determining their aerodynamic perfection are also given. The results of the work can be used in the development of helicopter profiles, direct and inverse problem solution to optimize their shapes, as well as in the process of performing calculations to determine the aerodynamic characteristics of helicopter propeller blade airfoils by CFD methods in the entire possible operational range of their operation at angles of attack and Mach numbers.


helicopter airfoil, computational fluid dynamics, aerodynamic characteristics


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