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Based on a two-dimensional object vorticity field unsteady aerodynamic calculation

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Tutor: LiuHong
School: Shanghai Jiaotong University
Course: Aircraft design
Keywords: Unsteady flow,Aerodynamic,Vorticity field,Vorticity momentum theorem
CLC: V211.4
Type: Master's thesis
Year:  2012
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In the study of the unsteady aerodynamic force mechanism in the process, hope to adopt the method of non-contact measurement wings in force in the process of the flapping wing movement. Non-contact measuring force is the key to stress the relationship between the flow field and object is established. Vorticity moment theorem and concise form is established in the whole flow field and vorticity a force moment and object relations. However, in the flow field information around an object known only limited areas, vorticity moment theorem is used to calculate the object force will encounter difficulties. Based on the vorticity moment theorem is deduced on the basis of the finite domain only using the velocity field and vorticity field calculation formula, the force applied on the object and gives the formula of the two different forms. In the numerical simulation of flow field using the formulas derived in this paper a formula and 2, respectively, to calculate the zero Angle of attack of 1000 Re no thickness plate, Re is 40 and 1000 of the stress of the cylinder, and the results are compared with those of the existing methods. The numerical results show that the two formulas derived in this paper can accurately reflect the limited domain objects bearing orders of magnitude. Control of body size calculation results have a certain impact. Outside the boundary layer in the name, along with the rising of the control volume, the results of two formulas derived in this paper can drop slightly.
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