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Wavefront distortion of hypersonic plate boundary layer under two-dimensional strip
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摘要:
二维粗糙带是常用的加速流场转捩的流动控制方式，理论分析并用风洞实验研究二维粗糙带作用下的高超声速平板边界层引起的波前畸变特性。采用波前检测系统测量高超声速边界层流场的波前畸变，对比有无粗糙带情况下的流场波前分布。研究结果表明，在高超声速平板边界层发生转捩以前，高精度波前测量系统不仅可以给出高速流场的波前分布，同时还可以计算对应的密度场。实验结果还表明，马赫数为5的边界层流场明显失稳时波前畸变有大幅度提高；同时通过对比有无粗糙带时波前畸变特点发现，平板壁面加粗糙带后尽管边界层的流态未发生变化，但相同位置的平均波前、波前均方根和峰谷值明显增大。
Abstract:Two-dimensional strip is a common flow control method to accelerate flow transition. The wavefront distortion resulting from hypersonic boundary layer has been investigated in virtue of theoretical analysis and wind tunnel experiments. Wavefront measurement system is used to measure the wavefront distortion of hypersonic boundary flow, and compare the distribution of flow wavefront with and without strip. The results prove that high-precision wavefront measurement system can present not only wavefront but also density distribution before the flow transition of boundary layer. In addition, the experimental results show that the wavefront distortion increases quickly when the flow is obviously unstable. Finally, comparing the distribution of wavefront induced by strip with the corresponding data without strip, we find that the mean wavefront, root mean square and peak-valley value of wavefront with strip are much larger than that without strip.
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Key words:
- wavefront /
- strip /
- hypersonic speed /
- plate boundary layer
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Aero-optical effects caused by hypersonic boundary layer transition are always challenges in improving the accuracy of directed energy weapon. In order to avoid hypersonic boundary transition in the optical detection window, which can generate large scale structures and cause wavefront distortion, researchers have tried many flow control methods to accelerate or delay transition. We investigate the effects of 2D strip to the hypersonic boundary layer in the virtue of theoretical analysis and wind tunnel experiments. A radial shearing interference system is used to measure the wavefront distortion
The experiment is conducted in FD-03 tunnel of China Academy of Aerospace Aerodynamics. Free stream total pressure is 1.05 MPa, total temperature is 350 K, Mach number is 5.01, Reynolds number is 2.45×107, and aerodynamic noise is 0.3%. We use plane model as an experimental model, the size of plane model is 250 mm×120 mm, the thickness of leading edge is 1 mm, and attack angle is 0. The plane is 30 mm above the bottom of the entrance of nozzle. The roughness is 0.8 μm~1.6 μm. The strip is attached on the plane 35 mm away from leading edge. The size of strip is 20 mm×120 mm×0.5 mm.
High-precision wavefront measurement system is used to measure the wavefront distortion of hypersonic boundary layer. This system based on the radial shearing interference system can measure the wavefront of flow filed precisely. We measure the wavefront of circular region with diameter of 0.9 mm and space of 3.9 mm, to reveal the development of hypersonic boundary flow and compare the distribution of wavefront induced by strip with the corresponding data without strip. After the calculation of data analysis program, we get the mean wavefront, root mean square and peak-valley value of wavefront, which are reflections of density distribution of hypersonic boundary flow.
The results prove that high-precision wavefront measurement system can present not only wavefront but also density distribution before the flow transition of boundary layer. In addition, the experimental results show that the wavefront distortion increases quickly when the flow is obviously unstable. Finally, comparing the distribution of wavefront induced by strip with the corresponding data without strip, we find that the mean wavefront, root mean square and peak-valley value of wavefront with strip are much larger than that without strip. It means the strip may accelerate the development of hypersonic boundary flow, and make the flow unstable earlier. The conclusions have some reference values to flow control of the guidance system on the hypersonic aircraft.
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图 5 平板边界层流场干涉图像. (a)无粗糙带. (b)有粗糙带.
Figure 5. Interference image of plate boundary flow. (a) Without strip. (b) With strip.
图 6 平板表面的波前畸变分布情况. (a) w值. (b) RMS值. (c) PV值.
Figure 6. Wavefront distortion distribution of flat surface. (a) w value. (b) RMS value. (c) PV value.
图 7 平板表面有无粗糙带的波前畸变对比图. (a) w值. (b) RMS值. (c) PV值.
Figure 7. Comparison of wavefront distortion of plate surface with and without strip. (a) w value. (b) RMS value. (c) PV value.
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