دانلود رایگان مقاله لاتین اثر پارامتر مبدل ضربه ای بر سطح کنترل از سایت الزویر
عنوان فارسی مقاله:
تاثیر پارامترهای مبدل ضربه ای بر سطح کنترل
عنوان انگلیسی مقاله:
Parameters effect of pulsed-blowing over control surface
سال انتشار : 2016
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مقدمه انگلیسی مقاله:
1. Introduction
Control surface, which is often located in the trailing edge of wings, is important in the attitude control of an aircraft. However, the efficiency of the control surface declines severely under the high deflect angle of the control surface because of the flow separation (see Fig. 1). This condition leads to the penalty of attitude control and limited aerodynamic performance of an aircraft. Therefore, suppressing the flow separation is considered in this study. Flow control [1] is the most available approach to achieve the goal of suppressing flow separation. In the past decades, scientists have exerted considerable effort to develop flow control techniques. Moreover, various flow control techniques have been used to suppress flow separation such as moving surface control technique [2–4], plasma flow control technique [5–8] and co-flow jet control technique [9–12]. Although flow separation on the control surface can be suppressed substantially by moving surface control technique or plasma flow control technique, the application of these techniques in engineering is limited because of complicated * Corresponding author. E-mail addresses: wangyankui@buaa.edu.cn (Y. Wang), shakazp@163.com (P. Zhou), sanqiu66@126.com (J. Yang). 1 Professor. 2 PhD student. 3 Master student. devices. For the co-flow jet control technique, a large amount of gas is necessary to suppress the flow separation. Thus, a powerful device is required to supply a high mass flow rate of jet. Recently, Wang et al. [13] developed a micro-blowing flow control technique to suppress the flow separation and improve the aerodynamic effi- ciency of the control surface. Wang et al. set a blowing airfoil (see Fig. 2) based on NACA0025 to demonstrate the micro-blowing flow control technique. A blowing slot that is normal to the boundary of flap was set near the leading edge of the flap. A high energy jet parallel to the upper surface of flap is injected to the main flow. The study shows that the flow separation can be suppressed by blowing at the leading edge of the flap. Moreover, the study shows that the maximum increment of lift coefficient of the flap can be 150%, while AOA (angle of attack) of the main wing is 0◦, the deflection angle of flap is 20◦ and the Reynolds number is 0.8 × 106. Wang et al. considered pulsed blowing to reduce the considerable gas requirement. Even though several researchers have also made improvements in development of the pulse jet technique to control the flow separation over the control surface [14,15], such technique is considerably more difficult to adopt in engineering because of lack of profound understanding of the fundamental mechanism and parameter similarity
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