提出一种基于多项式修正片条气动力的跨音速颤振分析方法，以片条内升力和力矩随攻角变化斜率为修正目标，采用多项式方程模拟片条力矩分布，使整个翼面的气动力大小和分布都与目标相符，进而使用修正后的气动力进行跨音速区的颤振分析。计算结果经跨音速颤振风洞试验验证，该方法对翼吊发动机构型的机翼颤振型、带操纵面的尾翼颤振型都有较高的计算精度，计算获得的跨音速压缩性“凹坑”特性与试验结果吻合较好。
Abstract
A transonic flutter analysis method based on modified strip aerodynamic force with polynomials was presented. Lift and moment slope in the strip were taken as the correction target. A set of polynomial equations were implemented to simulate the strip moment distribution to ensure the consistency of both the aerodynamic force and moment with their targets. The modified aerodynamic force is used in the transonic flutter analysis. Comparison with wind tunnel flutter tests of different configurations shown that the analysis results has high accuracy for both the wing-engine flutter mode and the stabilizer-rudder flutter mode. The transonic compressibility curve is consistent with the tests.
关键词
跨音速颤振 /
偶极子格网法 /
气动力修正 /
风洞试验
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Key words
transonic flutter, DLM /
aerodynamic correction, wind tunnel test
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