Influence of plasma actuators on aerodynamic characteristics of NACA 23012 airfoil


Аuthors

Suranov Y. S.1*, Umanskii A. O.1**, Murashov I. V.2***, Obraztsov N. V.1****

1. Peter the Great St. Petersburg Polytechnic University, 29, Polytechnicheskaya str., St. Petersburg, 195251, Russia
2. Ladoga-Energo LLC, Kirovsk, Leningrad region, Russia

*e-mail: jan.suranov@mail.ru
**e-mail: alex_umanskij997@mail.ru
***e-mail: iuriimurashov@gmail.com
****e-mail: obraztsov_nv@spbstu.ru

Abstract

Advances made in hardware and software systems for numerical simulation have helped improve the computational ac-curacy of aerodynamic characteristics of aircraft. The software used is a professional tool for engineering calculations, whose quality and capabilities determine the accuracy of the results obtained. The article reports on numerical study of the flight characteristics in an airfoil and influence of plasma actuators on it. The numerical study was carried out for the NACA 23012, determining the aerodynamic characteristics of the airfoil, i.e., drag and lift, via different software packag-es: COMSOL Multiphysics, ANSYS CFX and FlowVision. The mathematical model is based on stationary (RANS) and non-stationary (URANS) Reynolds equations.The presented results allow us to determine main software and the article is the first part of the study. Numerical simulation results and comparative analysis are presented for SST and k–ε turbulence models. The numerical models were validated based on the results of experimental studies. A dielectric bar-rier discharge (DBD) model and numerical simulation results are presented in the article.
The most consistent with the experimental data simulation results for the lift coefficient in the case of the RANS model were obtained using COMSOL Multiphysics incompressible formulation of the problem, RMSE is 1.4·10-3. A more accurate dependence of the drag coefficient on the angle of attack in comparison with the experimental data was obtained using ANSYS CFX, RMSE is 1.8·10-5.
According to the results of numerical simulation, the URANS model, despite high computational costs, allows obtaining more reliable results of aerodynamic characteristics at critical values of the angle of attack. RMSE of the lift coefficient for the URANS model is 8.4·10-2, and for the RANS model - 9.9·10-2. A numerical unified CFD and DBD model of the NACA 23012 airfoil was developed, and the assessment was performed taking into account the effect of dielectric barrier discharge and without taking into account the effect of DBD. The maximum increase in lift coefficient for the frequencies studied is up to 2% at 200 Hz, and the minimum decrease in drag coefficient is up to 8% at 1000 Hz.

Keywords:

airfoil, aerodynamics, dielectric barrier discharge, DBD, plasma actuator

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