1) blade-lift coefficient
桨叶升力系数
2) blade lift
桨叶升力
3) rotor blade improvement
桨叶升级
4) lift coefficient
升力系数
1.
Dealing with the problem of vortex induced vibration (VIV) of submarine pipe span with spoiler and focusing on the asymmetry of its lift coefficient, two new concepts are proposed: lift coefficient amplitude and lift coefficient additional value according to the special structure of spoiler.
然而对于带阻流板的管跨结构,由于其结构的特殊性,导致流场在绕流过程中产生的升力系数具有明显的非对称性。
2.
According to Navier Stokes equation, the lift coefficient and drag coefficient of the fiber were sug.
以振动纤维栅过滤除尘器中纤维为研究对象 ,通过实验研究结合流体诱发振动的机理分析 ,确定引起纤维振动的主要原因是流体绕流纤维时 ,旋涡脱落的不对称性产生的周期性升力作用于纤维 ,使纤维发生自激振动 ,旋涡脱落的频率与纤维的固有频率产生同步效应时旋涡脱落诱发纤维产生共振·当发生共振时 ,可以根据纳维斯托克斯方程计算出旋涡脱落产生的升力系数和阻力系数
3.
The aerodynamic loads and the maximum lift coefficient of the complete aircraft configuration (fuselage+wing+tail) are computed by using the modified three-dimensional low-order panel method in conjunction with the semi-empirical formulas of DATCOM.
同时使用一种由三维低阶板方法结合DATCOM方法半经验公式的改进方法预测复杂外形飞行器(机身+机翼+尾翼)的空气动力载荷和最大升力系数。
5) helicopter blade
直升机桨叶
1.
In the static strength analysis of helicopter blade,the traditional analysis method may lead to the uncertainty of the strength conclusion due to the inaccuracy of load calculation.
在直升机桨叶的静强度分析中,传统的分析方法可能会由于载荷计算的不准确,给强度结论带来不确定性。
2.
In this paper,the strength limit and fatigue limit of leading edge of a helicopter blade are obtained by tests of standard specimen,and stress concentration factors by finite element analysis.
通过标准样件试验,获得直升机桨叶前缘包铁的静强度极限和疲劳极限,通过有限元分析,获得应力集中系数,再应用应力集中系数对试验中获得的静强度极限和疲劳极限进行修正。
3.
Calculation about the natural vibration frequencies of the helicopter blade in rotating plane;
利用有限元法推导了直升机桨叶的耦合振动频率方程，提出了有效的计算方法──直接迭代法，并计算了桨叶第１至第４阶固有频率。
6) blade thrust
桨叶推力
补充资料：GS,GT型空心桨叶连续干燥机
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说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条