一种柔性机构实现后缘可变弯度翼型气动性能研究
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摘要
后缘可变弯度机翼是通过机构作动使机翼的后缘发生弹性形变从而改变机翼后缘外形。本文以SG_6043为基本翼型,通过一种可变弯度机构改变翼型后缘弯度,对不同变弯下的翼型进行CFD计算。结果显示后缘可变弯度翼型在一定的条件下可以提升机翼的升力,提高升阻比。
引文
1 Kota S.Shape Control of Adaptive Structures Using Compliant Mechanisms.Shape Control of Adaptive Structures Using Compliant Mechanisms,2000.
2 Hetrick J A.Design and Application of Compliant Mechanisms for Morphing Aircraft Structures.Proceedings of SPIE-The International Society for Optical Engineering,2003,5054:24-33.
2 Hetrick J A.Design and Application of Compliant Mechanisms for Morphing Aircraft Structures.Proceedings of SPIE-The International Society for Optical Engineering,2003,5054:24-33.