Experimental studies on flaps flow-around active control by semi-model of the supersonic passenger aircraft wing

Aeronautical and Space-Rocket Engineering


DOI: 10.34759/vst-2022-4-22-35

Аuthors

Sha M. 1*, Sun Y. 2**, Li Y. 1***

1. Northwestern Polytechnical University, 710072, 127, West Youyi Road, Beilin District, Xi'an Shaanxi, P.R.China
2. Hangzhou Xiaoshan Technician College, Department of Mechanical Engineering, Hangzhou City, 311200, People’s Republic of China

*e-mail: shamg2020@nwpu.edu.cn
**e-mail: 544974488qq.com
***e-mail: liyulong@nwpu.edu.cn

Abstract

The wing of modern aircraft is one of the objects of control. Depending on the purpose, type, class and aerodynamic layout of the aircraft, it is equipped with various means of mechanization — devices and systems designed to control aerodynamic characteristics without changing the angular position of the aircraft in the stream. Mechanization is used at all stages of flight: during takeoff, climb, cruising, level change, descent, landing approach, movement along the glide path, landing and landing run. In order to increase the lift force for a supersonic passenger aircraft in takeoff mode, a blown flaps control device has been developed, that is, near the trailing edge of the wing, it is carried out by imparting additional kinetic energy to the retarded flow by blowing off the boundary layer with a gas jet. This article presents the results of an experimental study of the influence of the jet momentum coefficient and the flap deflection angle on the lift coefficient СL and the drag coefficient СD. Using the PIV (Particle Image Velocimetry) observation system, the flap blowing control mechanism was studied. The lift measurement results show that is too large to effectively increase СL when air circulation control is not applied, while the effective can be increased after air circulation control is applied. The maximum lift force of the model wing can be obtained with a small and = 30°, and with an increase in , the maximum point of the lift force of the model gradually shifts back at = 40°. The results of the PIV experiment show that in the absence of airflow control on the surface of the flaps, a clear flow separation is observed, and after turning on the flow control at = 30°, the flow reattachment can be completed with a small . With an increase in , the flow velocity on the upper surface of the wing further increases; when is less than 0.04 and = 40°, the flow joins, at which СL and СD increase; when is greater than 0.04, the flow joins, at which СL increases, and СD decreases, the lift-to-drag ratio K increases, and the aerodynamic characteristics improve significantly.

Keywords:

blow flaps, increase, flow control, wind tunnel experiments, PIV

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