Investigation of the effects of angle of attack and tail deflection angle on the controlling tail flow field
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ORIGINAL PAPER
Investigation of the effects of angle of attack and tail deflection angle on the controlling tail flow field Ali Mokhtari1 · Azadeh Shahrian2 · Pooya Javadpoor Langroodi1 · Maryam Ghodrat3 Received: 4 April 2020 / Revised: 6 September 2020 / Accepted: 19 September 2020 © Shanghai Jiao Tong University 2020
Abstract In the current study, the flow behavior due to the variation of the tail angle of attack and its deflection has been investigated on a body–tail with a controlling tail. Numerical computations were carried out at a constant velocity of 90 m/s with the tail angle of attack and deflection ranging from 0 to 30 degrees. It provides a deeper understanding of how the aerodynamics of the tail is influenced by the deflection of the tail and the variation of the angle of attack, along with body and nose vortices. The formation of structure and breakdown of vortices along with their effects on the pressure distribution over the tail and the corresponding normal force coefficients derived from the numerical results. As a result, due to increasing the angle of attack or the deflection angle, the high-pressure area extends over the surface of the controlling tail facing the flow. Besides, the effects of angles of attack on the normal force coefficients on the tail are more than deflection angles due to body effects and the corresponding generated vortices. A comparison of numerical results and experimental tests showed satisfying accuracy and provided reliable details on the flow behavior and the highest calculated error rate was 12.8%. Keywords Angle of attack · Body–tail · Vortices · Pressure distribution · Deflection angle · Normal force coefficient
1 Introduction The need for higher maneuverability of aircraft grows every day, which signifies the importance of flow field investigation over tail or control tail for various flight conditions. Many studies have been done to numerically and experimentally address the effects of the body and its vortices and other factors on the tail performance. Interactions between different components of an aircraft in different flight conditions are very important. These interactions will increase at higher angles of attack, so in the flying vehicles controlled by their tail, tail design and flow analysis of the tail are critical and have a significant impact on the aircraft performance. For example, for a body–tail con-
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Maryam Ghodrat [email protected]
1
Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran
2
Department of Aerospace Engineering, Islamic Azad University, Science and Research Branch, Tehran, Iran
3
School of Engineering and Information Technology, University of New South Wales Canberra, Canberra, ACT 2610, Australia
figuration (the model studied in the present study), a certain amount of lift must be achieved with an appropriate ratio of the tail deflection angle to the body angle of attack [1]. Flow field investigations for various flow conditions inside different wind tunnels were conducted and differen
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