Non-intrusive estimation of the buffet loads on a supercritical airfoil with SCBs

IF 2.3 3区 工程技术 Q2 ENGINEERING, MECHANICAL
A. D’Aguanno, A. Corduas, F. F. J. Schrijer, B. W. van Oudheusden
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Abstract

This study experimentally investigates the effect of three-dimensional shock control bumps (SCBs) on the aerodynamic loads of a supercritical airfoil under transonic buffet conditions. The experiments consisted in planar particle image velocimetry (PIV) measurements and have been carried out in the transonic-supersonic wind tunnel of TU Delft under fully developed buffet conditions (\(\text {Ma}=0.7\) and \(\alpha =3.5^{\circ }\)). The bumps are wedge-shaped and have been placed in the center of the shockwave oscillation range. Shock detection and phase-averaged velocity fields confirm that properly designed and spaced (\(\Delta y_\text {SCB}/c = 25\%\)) SCBs reduce the shockwave oscillation range (compared to the clean case). The velocity data have been further used to evaluate the pressure field around the entire airfoil, and afterward, lift and drag coefficients have been retrieved, respectively, from momentum contour and wake integral approaches. Results demonstrate that SCBs have a beneficial effect on the aerodynamic loads with an increase in lift and a decrease in drag under fully developed buffet conditions. More importantly, a strong reduction of the amplitude of oscillations of both lift and drag coefficient, within the different buffet phases, was noted. Tests at multiple spanwise locations revealed relevant differences, with lower drag and higher lift values being achieved in the symmetry plane of a SCB, while a worse performance (with values comparable to the clean case) was achieved in the symmetry plane in between two adjacent bumps.

带scb的超临界翼型冲击载荷的非侵入式估计
实验研究了跨声速冲击条件下三维冲击控制突对超临界翼型气动载荷的影响。实验包括平面粒子图像测速(PIV)测量,并在代尔夫特工业大学跨声速-超音速风洞中在充分开发的冲击条件下进行(\(\text {Ma}=0.7\)和\(\alpha =3.5^{\circ }\))。凸起是楔形的,被放置在冲击波振荡范围的中心。冲击检测和相平均速度场证实,合理设计和间隔(\(\Delta y_\text {SCB}/c = 25\%\))的scb减少了冲击波振荡范围(与干净的情况相比)。速度数据进一步用于评估整个翼型周围的压力场,然后,升力和阻力系数分别从动量轮廓和尾迹积分方法中得到。结果表明,在充分发展的冲击条件下,SCBs对气动载荷有有利的影响,升力增加,阻力减少。更重要的是,研究人员注意到,在不同的自助餐阶段,升力系数和阻力系数的振荡幅度都大大减小了。在多个跨向位置进行的测试显示了相关差异,在SCB的对称平面上实现了较低的阻力和较高的升力值,而在两个相邻凸起之间的对称平面上实现了较差的性能(其值与干净的情况相当)。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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来源期刊
Experiments in Fluids
Experiments in Fluids 工程技术-工程:机械
CiteScore
5.10
自引率
12.50%
发文量
157
审稿时长
3.8 months
期刊介绍: Experiments in Fluids examines the advancement, extension, and improvement of new techniques of flow measurement. The journal also publishes contributions that employ existing experimental techniques to gain an understanding of the underlying flow physics in the areas of turbulence, aerodynamics, hydrodynamics, convective heat transfer, combustion, turbomachinery, multi-phase flows, and chemical, biological and geological flows. In addition, readers will find papers that report on investigations combining experimental and analytical/numerical approaches.
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