摘要
本文提供了在FL-23风洞中进行的试验研究结果。试验采用动力相似的四种不同尺寸的60°三角机翼平板半模型。结果表明:洞壁干扰提高了跨声速颤振临界速压,当模型展长对试验段宽度的比值Lm/B为0.687、0.600和0.512时,使颤振临界速度的压缩性修正系数分别减小3.8％、2.5％和1.4％。改变开孔率的试验定性验证了上述结果的合理性。
This paper gives the results of experimental investigation in FL-23 wind tunnel. Four dynamically similar plate half-models of a 60° delta wing in various sizes were used in the tests. The results showed that the critical transonic flutter dynamic pressure was increase'd by the wind tunnel interference, and that when the ratios of the model span to the tunnel width is 0.687, 0.600 and 0.512, the compressibility correction coefficient to the critical flutter velocity was reduced by 3.8%,2.5% and 1.4%, respectively. Variable porosity tests qualitatively demonstrated the abovementioned results.
出处
《空气动力学学报》
CSCD
北大核心
1989年第3期351-357,共7页
Acta Aerodynamica Sinica
关键词
风洞
洞壁
跨声速
颤振
干扰
wind tunnel wall interference, flutter test, transonic test.
