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首页> 外国专利> METHOD FOR EXPERIMENTAL DETERMINATION OF AERODYNAMIC CHARACTERISTICS OF A MODEL DURING QUASI-STATIC TESTS IN A WIND TUNNEL

METHOD FOR EXPERIMENTAL DETERMINATION OF AERODYNAMIC CHARACTERISTICS OF A MODEL DURING QUASI-STATIC TESTS IN A WIND TUNNEL

机译：风洞中模型静态试验的气动特性试验确定方法

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FIELD: aviation.;SUBSTANCE: invention relates to experimental aerodynamics of aircraft during experimental research in a wind tunnel. Method consists in that the analyzed model is installed in the working part of the aerodynamic pipe on the supporting device. No flow is measured. After the pipe is set to the operating mode (preset flow rate is set) with the help of the drive, the model is moved along the angle of attack (sliding) from the initial to the specified final angle and back. Indications of aerodynamic scales, an angle of attack (slip) sensor and a pressure sensor with sampling frequency of not less than 1 kHz are recorded simultaneously with the beginning of movement and to its end. Further processing involves taking detrimental aerodynamic loads from measured readings, which are filtered with a Butterworth low-pass filter with cutoff frequency of 2–5 Hz. As a result, obtaining quasi-static aerodynamic dependencies, from which position of "catastrophic" transitions on angles of attack (slip), as well as angles of attack (slip) of the beginning of aerodynamic shaking and its development on angles of attack (slip) are determined.;EFFECT: location of features in the form of "catastrophic transitions" in aerodynamic characteristics, as well as in determination of angles of attack and sliding at which "pre-threshold" aerodynamic shaking and its development with increase of these angles begins to appear.;1 cl, 7 dwg
机译：技术领域本发明涉及在风洞中进行实验研究期间飞机的实验空气动力学。方法在于，将分析的模型安装在支撑装置上的气动管的工作部分中。没有测量流量。在借助驱动器将管道设置为工作模式（设置预设流速）之后，将模型沿着迎角（滑动角）从初始角度移动到指定的最终角度，然后返回。在运动开始时和运动结束时同时记录空气动力学刻度，迎角（滑移）传感器和压力传感器的采样频率不低于1kHz。进一步的处理涉及从测量的读数中获取有害的空气动力学负载，这些负载由具有2–5 Hz截止频率的Butterworth低通滤波器进行滤波。结果，获得了准静态的空气动力学相关性，从该位置开始，“大灾难”的位置在迎角（滑移）上过渡，以及气动振动开始时的迎角（滑移）及其在迎角上的发展（效果：在空气动力学特征中以“灾难性转变”形式出现的特征的位置，以及在确定“阈值前”空气动力学摇动的迎角和滑动角及其随这些角的增加而发展的位置角开始出现。; 1 cl，7 dwg

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