The Joukowski airfoil problem is the simplest application of conformal mapping to airfoil design.
joukowski問題是最簡單的翼型形映射應(yīng)用到機翼設(shè)計.
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An effective aerodynamic optimization design method of transonic airfoil is given.
提出了一種有效的跨音速翼型氣動優(yōu)化設(shè)計方法.
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In the design page, submit the form to design the first airfoil.
在設(shè)計頁, 遞交表格設(shè)計第一翼型.
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The numerical algorithm is applied for flow over an NACA 0012 airfoil with satisfactory effect.
經(jīng)對繞NACA0012翼型無粘流動計算的驗證,收效明顯.
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The high speed airfoil type wind turbine has the highest efficiency in high wind speeds.
高速機翼型風(fēng)輪機在高風(fēng)速下達(dá)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++進(jìn)行編程,從而模擬FRP飛機機翼FW成型 整個過程.
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Airfoil flutter is one of the important problems in aeroelasticity.
在氣動彈性力學(xué)中,機翼振顫是一個非常典型的問題.
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In this regard, several are given based on existing designs, eg, the SD 7037 airfoil and others.
在這方面, 有幾個版本,基于現(xiàn)有翼型設(shè)計,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.
網(wǎng)上版的代碼允許處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翼型動態(tài)測壓的實驗結(jié)果,初步分析了影響翼型動態(tài)氣動特性的因素.
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The given airfoil is then analyzed to determine, say, its velocity distribution.
由于機翼的分析,以確定那是說, 它的速度分布.
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A supporting surface of an airplane ; an airfoil a wing.
飛機有后掠翼的圓滑的機翼.
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The problem of unsteady separated flow of rapidly pitching airfoil with oscillating motion is computationally studied.
對帶振蕩的快速上仰翼型的非定常分離流問題進(jìn)行了計算研究.
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How does the brake act on the paraglider airfoil?
剎車是如何作用于滑翔傘的翼型?
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Two pieces of foam are sandwiched onto the center piece and sanded to an airfoil shape.
兩件是泡沫夾心到中心片和磨光的機翼形狀.
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The properties of bifurcation points of airfoil flutter with cubic nonlinearity in incompressible flow are studied.
對定?？諝鈩恿ψ饔孟隆⒑⒎椒蔷€性剛度的二元機翼顫振系統(tǒng)的分叉點進(jìn)行了研究.
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A supporting surface of an airplane ; an airfoil or a wing.
飛機尾部組成部分的垂直機翼.
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The mathematical transformation is fixed and the airfoil is moved to generate different airfoil geometries.
數(shù)學(xué)變換是固定機翼的翼型幾何移到產(chǎn)生不同.
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The airfoil shape is then adjusted until the desired velocity distribution is obtained.
然后是調(diào)整翼型的形狀,直到取得預(yù)期的速度分布.
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