naca

Two dimensional simulation of the transonic flow over NACA 0012 airfoil

二维翼型跨音速绕流的数值模拟

Measurements of unsteady pressure distribution on a NACA 0012 profile in transonic flow

NACA0012翼型跨音速非定常压强分布的测量

An experimental investigation on location of boundary layer transition on the NACA 0012 using surface hot film gages

应用表面热膜测定NACA0012翼型边界层转捩区位置的实验研究

The NACA , before NASA , never developed an airliner and never ran an airline .

美国航空资讯委员会，在美国国家宇航局之前，从未开发过客机，而且从未运营过航空线。

Glaze ice accretion on the leading edge of the NACA 0012 airfoil is predicted using CFD method .

本文采用计算流体力学的方法对NACA0012翼型前缘涉及传质传热效应的glazeice积冰进行了预测。

This paper shows the wind tunnel testing results of NACA four symmetrical airfoil Section cascades of Wells turbine for wave energy conversion .

本文介绍用于波能转换的威尔斯涡轮的NACA四位数对称叶型叶栅的风洞试验结果。

The Bell X-5 gave NACA and Air Force researchers a chance to test out variable-sweep wings .

在贝尔X-5和空军赋予的NACA研究人员一个机会来测试可变后掠翼。

Calculations show that the cavitation-free bucket diagram of new blade sections is wider than the conventional NACA sections .

计算结果表明新剖面螺旋桨方案的空泡斗要比常规剖面的宽。

" Nobody wanted to fly the XF-92 ," NACA test pilot Scott Crossfield said .

“没有人想要飞翔的XF型-92”的NACA试飞员斯科特菲尔德说。

Tip vortices generated from a rectangular half-span wing model ( NACA 0012 ) have been experimentally investigated .

采用激光粒子成像速度仪（PIV）对一矩形机翼（NACA0012）模型所产生的翼梢涡进行了风洞测试研究。

The Numerical Simulation of the Flow Around the Rudder with NACA Airfoil Section and the Computer Aided Design of the Semi-spade Rudder

NACA半悬挂舵舵叶流场数值模拟及舵装置辅助设计

One the basis of the structure , we found a novel nucleic acid-binding region on the a subunit of NAC ( NACA ) .

在此基础上，我们发现了aNAC亚基（NACA）上的一个新的核酸结合区域。

The flow field around NACA 0012 airfoil with software Fluent was simulated , to compare the correspondent aerodynamic performance variation before and after icing .

本文用FLUENT软件模拟了结冰后NACA0012翼型周围流场的变化，并与结冰前NACA0012翼型的气动性能进行了对比。

Using present method in the conditions of zero attack-angle and transonic flow a bicircular-arc , NACA 0012 and 10 % R.

迭代的收敛性很好。用本文方法在零攻角和跨音速绕流的条件下计算了双圆弧翼型、NACA0012翼型和R。

The algorithm developed in this paper was used to simulate the 2D large scale separation flow field of NACA 0012 airfoil . , and the computation results accorded with experienced results very well .

利用所给出的算法对NACA0012翼型二维大尺度分离流场进行了计算，计算结果和实验结果基本一致。

The inlet flow angle and diviation angle were confirmed which was applied to low cascade experiment result of American NACA , and controlled diffuser factor and flow deflection angle in design .

并应用美国NACA低速叶栅试验结果确定流入角和落后角，设计中控制扩散因子和气流折转角。

A design method for diagonal-flow impeller based on the quasi-three-dimensional theory and by means of flat cascade data of NACA as well as the concept of axial-flow impeller is presented .

本文根据准三元理论，利用NACA平面叶栅资料，以轴流式叶轮的研究方法为出发点，提出了斜流叶轮的设计方法。

There are many types of sails on modern sail-assisted ships , according to the characteristics of squid fishing vessels ; we choose NACA and arc-shaped sail as research sail model .

现代助航风帆类别有很多种，根据鱿鱼钓船的特点，本文选择了NACA型和圆弧型两种风帆作为辅助帆型。

NASA , previously the National Advisory Committee for Aeronautics ( NACA ), was created largely in response to the Soviet Union 's launch of Sputnik in1957 .

前身为国家航空咨询委员会，主要为因应1957年苏俄发射第一枚人造卫星「史波尼克号」而创立。

Heading up the design team was Smith J.de France , an engineer for NASA 's predecessor , the National Advisory Committee for Aeronautics ( NACA ) .

标题了史密斯j的设计团队法国，美国航空航天局的前身，为国家航空咨询委员会（NACA）的工程师。

Through the immunofluorescence assay in vivo , we discovered that this nucleic acid-binding region is crucial for the location of the NACA homodimer in the nucleus .

通过胞内免疫荧光实验观察，我们发现这个核酸结合区域对NACA同源二聚体在细胞核内的定位有关键作用。

Dressed warmly , an unnamed NACA test pilot in1928 gets ready for a high-altitude flight from the group 's Langley Memorial Aeronautical Laboratory airfield in Virginia .

穿着热烈，于1928年1无名的NACA试飞员得到准备从该集团的兰利航空实验室在纪念弗吉尼亚机场高空飞行。

To study the influence of initial fields on computation results , the author , starting from two-dimensional steady transonic small disturbance equation , has computed NACA 0012 airfoil by the mixed finite-difference relaxation iteration method .

为研究初场对计算结果的影响，本文从二元定常跨音速小扰动方程出发，用混合有限差分松弛迭代法对NACA0012翼型作了计算。

Extensively collected and analysed dominant wind turbine dedicated airfoils , and based on the application of NACA airfoil on wind turbine , compared and analysed the geometric features 、 aerodynamic characteristics and applicable wind turbine types .

广泛收集和分析了现有的风机专用翼型，并以NACA经典翼型在风机上的应用为基础，对比分析了各风机专用翼型的几何特点、气动特性和适用机型。

Compressible flow around an NACA 0012 airfoil at high angle of attack is numerically simulated by solving the two-dimensional Navier-Stokes equations in a body-fitted system , the grid system is C-type grid generated algebraically .

以求解二维N-S方程数值模拟NACA0012翼型大攻角状态的可压绕流特性；N-S方程是在贴体坐标系中给出的，以代数方法生成C型网格系统。

The computational grid is C and C H types in a body fitted coordinate system generated by an algebraical method . The transonic viscous flows around the NACA 0012 aerofoil and M6 wing with pitching oscillation have been calculated .

分别计算了NACA0012翼型和M6机翼作俯仰振荡时跨音速非定常粘性绕流流场。研究了非定常绕流的气动特性。

Finally , results of numerical computation are given for NACA 0012 aerofoil in lifting and non-lifting flows with and without shocks , and are compared with some other numerical results , which shows that the present method is a good one for numerical accuracy and computational economy .

最后给出了NACA0012翼型在有无升力和有无激波各种状态下的计算结果。比较表明，本方法的计算结果与其它方法的计算结果符合得较好，且计算量很小。