可变形儒可夫斯基翼型非定常气动力的研究.pdfVIP

第 30 卷第4 期 Vol. 30 No .4 力学象11 2009 年 12 月 CHINESE QUARTERLYOF MECHANICS Dec. 2009 可变形儒可夫斯基翼型非定常气动力的研究 王晓宏，赖李健，高彦峰 〈中闰科学技术大学热科学和能源工程系.安做合肥 230026) 摘要:对于摞而变形法向运动速度远小子来流i集度的儒ñT夫斯蜷饥冀，将解析解和离散涡方法相综合计算变形 机冀的流场及非定常气动力，校详细地分析了变形机翼升力系数的准定常计算方法的误经来源，并给tI\修正方 法.计算结果显示脱落涡足迹对升为系曼史和饥冀绕流环量的影响很小，变形机翼升力系数准定常汁革方法的误 差毛要来源于流体非.):Ë常运动引起的虚拟质锺力.ì$非定常附加升力仅与当前J时刻飞行姿态及.~形状和1 51:形 速率有关.与具体的变形历史过程无关.i:形t1L冀的升为近似等于准定常计算综巢叠加上相应的虚拟质量力. 关键词:智能飞行糯g 可变形飞行;儒可夫斯基翼!12.气动力s 准定常假设，!l拟质量为 申图分类号: V21 1.41 文献标iR码:A 文.编号:0254-0053(2009)04-495-08 Study on Un steady Aerodynamic Force of Morphing Joukowski Aírfo il WANG Xíαo-h01叨.LAl Li-jiα饨 .GAO Yan拘叼 Department 01 Thennal Science and Energy Engineering. University of Science and Technology of Chioa. Hefei. Al由ui 230026. China) Abstract; AS5uming that the norma l deformation ve locity on the wing surface is much smaller than (ree stream velocity. the un5teady flow field and aerodynamic Iift for the morphing Joukowski airfoil were cal - culated by combining the analytical solution and the discrete vortex me lhod tοgether. The e rror sources of qua5i-steady assumption were analyzed rigorously and correspondingly the error correction method was proposed . The numericalωIculations show that the vortex wake of morphing airfoil has almost no effect on the lift coefficient and the circulation around the airfoil. The additional unsteady aerodynarnic Iift caused by the virtual mass force i5 the main error source of quasi-steady solution for the aerodynamic Iift of morphing airfoi l. 1t is also shown that the flight attitude , the airfoil profiles alld the deform