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Shang Tai, Lixin Wang, Yanling Wang, Shiguang Lu, Chen Bu and Ting Yue
In the early stages of aircraft design, a scaled model of the aircraft is installed in a wind tunnel for dynamic semi-free flight to approximate real flight, and the test data are then used to identify the aerodynamic parameters. However, the absence of ...
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Lixin Wang, Shang Tai, Ting Yue, Hailiang Liu, Yanling Wang and Chen Bu
The wind tunnel virtual flight test realizes the dynamic semi-free flight of the model in the wind tunnel through the deflections of the control surface and uses the test data to identify the aerodynamic derivatives. The difference in dynamics between th...
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Fei Xue, Yunlong Zhang, Ning Cao and Liugang Li
In this paper, unsteady motion tests of a lateral jet adjusting an air vehicle?s attitude are carried out. Curves of pitch moment amplification factors (KM) for a lateral jet versus angle of attack (a) are obtained using a wind tunnel free-flight test te...
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Changkun Yu, Zhigang Wu and Chao Yang
With the increasing bandwidths of servo control systems and decreasing mode frequencies, aeroservoelastic (ASE) stability evaluation has become an essential part of flight vehicle design. However, the theoretical method is limited by the modeling errors ...
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Christian Franzmann, Friedrich Leopold and Christian Mundt
An experimental method for the determination of the pitch damping moment coefficient sum ??????+???????
C
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q
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a
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in a wind tunnel at transonic and low supersonic Mach numbers is developed. With support interference being a major issue for dynamic...
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