英语论文结论部分写作特点总结

1、英语论文写作论文结论部分（Conclusion）写作特点总结ConclusionConclusion是作者对所研究课题进行的总体性讨论，具有严密的科学性和客观性，反映本研究课题的价值，同时对以后的研究具有指导意义。Conclusion与Introduction遥相呼应，因为Introduction部分介绍了本课题的研究目的，那么Conclusion要告诉读者这些目的是否达到，在研究中做了哪些工作，取得了什么结果，这些结果说明了什么问题，有何价值和意义，研究过程中存在或发现了哪些问题，原因是什么，建议如何解决等。Conclusion的具体内容通常包含以下几个部分：(1) 概括说明本课题的研究内容、结果及其意义与价值。(2) 比较具体地说明本研究证明了什么假设或理论，得出了什么结论，研究结果有何实用价值，有何创造性成果或见解，解决了什么实际问题，有何应用前景等。(3) 与他人的相关研究进行比较。(4) 本课题的局限性、不足之处，还有哪些尚待解决的问题。(5)展望前景，或指出进一步研究的方向。Conclusion通常使用现在时态Result和Conclusion本次选取5篇文章，第一篇，论文

2、中的主要Result已在第2部分和第三部分中叙述，在Conclusion又重新总结了一下。第二篇，论文中的主要Result写在 Conclusion中。第三篇，论文中的主要Result写在第3部分（3.CASE STUDIES AND RESULTS）中，Result和Conclusion是分开的。第四篇，论文中的主要Result已第4部分的（IV. Results and Discussion）中进行叙述， Result和Conclusion是分开的。第五篇，论文中的主要Result已第4部分的（4. Results and discussion）中进行叙述， Result和Conclusion是分开的。第1篇题目：An overview of NACA 6-digit airfoil series characteristics with reference to airfoils for large wind turbine blades请预览后下载！IV. ConclusionsThe two-dimensional aerodynamics characteristics o

3、f the NACA 63 and 64 six-digit series of airfoils measured in the NASA LTPT have been investigated, with a view to verify RFOIL calculations at high Reynolds numbers. The following conclusions can be drawn: - The zero-lift angle of the NACA 64-618 airfoil needs to be adjusted with -0.4 degrees. - The zero-lift angle of The NACA 63-615 needs to be corrected with -0.87 degrees in the smooth case and with +1 degree in case of wrap around roughness. -The maximum lift coefficients predicted with RFOI

4、L match the LTPT data well at Re=3x106, but under predict the Cl,max at Re=6x106 by 3.5 % , up to 6.5% at Re=9x106. -It is uncertain if the established differences in lift between experiment and calculations are caused by a constant bias in the measurements or by the fact that the RFOIL code fails to predict the right level of maximum lift. -RFOIL consistently under predicts the drag coefficient. The difference is about 9% for a wide range of airfoils and Reynolds numbers -NACA standard roughnes

5、s causes a reduction in the lift coefficient of 18% to 20% for most airfoils from the NACA 64 series -The zero-lift angle of airfoil NACA 64-418 with wrap-around roughness needs a correction of +0.54 degrees. -Wind tunnel experiments and side-by-side tests in the field with one clean rotor need to be done to be able to better predict the effects of roughness.写作特点：内容：第1句，概括了文章的的主要研究内容。第2句至第8句逐条的列出了文章的得出结论。使用了被动语态，The two-dimensional aerodynamics characteristics of the NACA 63 and 64 six-digit ser

6、ies of airfoils measured in the NASA LTPT have been investigated have been investigated.主要时态为一般现在时态请预览后下载！第2篇题目： HIGH-LIFT ENHANCEMENT USING ACTIVE FLOW CONTROLV. CONCLUSIONSThe high-lift performance of an airfoil with a single-element flap is enhanced significantly using an active flow control system consisting of spanwise fluidic actuators that are integrated near the separation point. Spanwise arrays of spanwise-oscillating or non-oscillating jets issue tangentially to the local surface from

7、a miniature downstreamfacing surface step. Jet actuation leads to flow attachment of varying streamwise extent that depends on the jet momentum coefficient and the formation of a low pressure domain near the juncture between the main body and the flap. As a result, lift is increased substantially, by as much as DCL = 1.40, 1.22 and 1.04 at Rec = 6.7105, 8.3105and 1.0106, respectively, for = 4.In the present experiments, three spanwise rows of fluidic jets are placed in the vicinity of the junctu

8、re and operated in various combinations leading to significant increases in lift. The upstream (x/c = 0.59) and middle (x/c = 0.61) actuators, which are closest to separation (x/c = 0.62) are most effective, while the downstream actuator (x/c = 0.64) only produces a significant lift increment when operated in conjunction with one of the other actuators. The degree of flow attachment increases with jet momentum coefficient and simultaneous operation of multiple actuators can increase the lift inc

9、rement further even when the flow is attached. Actuation results in a strong suction peak near the juncture (Cp 7.5) and also leads to increases in suction on the main body of the airfoil and near the leading edge. The lift increment is measured over a range of angles of attack (0 12) and is accompanied by an increase in lift-induced pressure drag and an increase in nose-down pitching moment. It is shown that the high-lift performance can be improved significantly by design modifications of the surface interface between the jet actuators and the surrounding flow. In particular, modifying the jet orifices from a “stepped” to a “recessed” configuration enhances the interaction of the jets with the cross flow, resulting in increased lift for a given momentum coefficient, particularly at lower levels of Cm. The recessed design also reduces the loss in lift cause

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