3维失速团对层流NACA64 -418翼型压力分布的影响

2016/11/17   下载量： 6 次

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飞行器空气动力学领域关于3维失速团和翼型压力关系的研究报告。发表在实验流体上《Exp Fluids》2016年第57卷。

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A 3D stall-cell flow-field has been studied in
a 4.8 aspect-ratio wing obtained by linear extrusion of a
laminar NACA64-418 airfoil profile. The span-wise change
in the velocity and pressure distribution along the wing has
been quantified with respect to the development of cellular
structures from 8◦ to 20◦ angle of attack. Oil-flow visualizations
help localizing the regular cellular pattern in function
of the angle of attack. Multi-plane stereoscopic PIV
measurements obtained by traversing the entire setup along
the wing span show that the flow separation is not spanwise
uniform. The combination of different stereoscopic
fields into a 3D volume of velocity data allows studying the
global effect of the stall-cell pattern on the wing flow. Integration
of the experimentally computed pressure gradient
from the Navier–Stokes equation is employed to compute
the span-wise distribution of the mean surface pressure.
Comparison of the results with the ones obtained from
pressure taps installed in the wing evidences a span-wise
periodic loading on the wing. The periodic loading has
maxima confined in the stream-wise direction between the
location of the highest airfoil curvature and the one of the
airfoil flow separation. Estimation of the periodic loading is
found within 2–6 % of the sectional wing lift.

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