The Joukowski airfoil problem is the simplest application of conformal mapping to airfoil design.
joukowski问题是最简单的翼型形映射应用到机翼设计.
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An effective aerodynamic optimization design method of transonic airfoil is given.
提出了一种有效的跨音速翼型气动优化设计方法.
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In the design page, submit the form to design the first airfoil.
在设计页, 递交表格设计第一翼型.
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The numerical algorithm is applied for flow over an NACA 0012 airfoil with satisfactory effect.
经对绕NACA0012翼型无粘流动计算的验证,收效明显.
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The high speed airfoil type wind turbine has the highest efficiency in high wind speeds.
高速机翼型风轮机在高风速下达到最高的使用效率.
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Lastly, the paper programs to simulate FRP airfoil FW moulding by VC ++.
最后, 本文用VC++进行编程,从而模拟FRP飞机机翼FW成型 整个过程.
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Airfoil flutter is one of the important problems in aeroelasticity.
在气动弹性力学中,机翼振颤是一个非常典型的问题.
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In this regard, several are given based on existing designs, eg, the SD 7037 airfoil and others.
在这方面, 有几个版本,基于现有翼型设计,例如, sd7037翼型等.
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The Web version the code allows for the prescription the inviscid velocity distribution about the airfoil.
网上版的代码允许处方粘速度分布的翼型.
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The experimental results of NACA 0012 airfoil dynamic pressure measurement are given here.
12翼型动态测压的实验结果,初步分析了影响翼型动态气动特性的因素.
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The given airfoil is then analyzed to determine, say, its velocity distribution.
由于机翼的分析,以确定那是说, 它的速度分布.
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A supporting surface of an airplane ; an airfoil a wing.
飞机有后掠翼的圆滑的机翼.
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The problem of unsteady separated flow of rapidly pitching airfoil with oscillating motion is computationally studied.
对带振荡的快速上仰翼型的非定常分离流问题进行了计算研究.
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How does the brake act on the paraglider airfoil?
刹车是如何作用于滑翔伞的翼型?
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Two pieces of foam are sandwiched onto the center piece and sanded to an airfoil shape.
两件是泡沫夹心到中心片和磨光的机翼形状.
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The properties of bifurcation points of airfoil flutter with cubic nonlinearity in incompressible flow are studied.
对定常空气动力作用下、含立方非线性刚度的二元机翼颤振系统的分叉点进行了研究.
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A supporting surface of an airplane ; an airfoil or a wing.
飞机尾部组成部分的垂直机翼.
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The mathematical transformation is fixed and the airfoil is moved to generate different airfoil geometries.
数学变换是固定机翼的翼型几何移到产生不同.
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The airfoil shape is then adjusted until the desired velocity distribution is obtained.
然后是调整翼型的形状,直到取得预期的速度分布.
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