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lifting-surface
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  升力面
     A design method for ducted propellers by coupling RANS solver with lifting-surface method
     与粘流耦合的导管螺旋桨升力面设计方法
短句来源
     A refinement in the treatment of boundary value problem of propeller lifting-surface theory
     螺旋桨升力面理论边值问题的精细化处理
短句来源
     Based on the theory of potential flow,steady lifting-surface theory and the potential based low-order surface panel methodi the mathematical models for predicting the performance of the HD propeller and MAU propeller are respectively established in this paper,and the numerical calculations are alsocarried out.
     本文首先基于势流理论和定常螺旋桨的升力面理论,以及基于速度势的低阶面元法理论建立了沪东型(HD)螺旋桨和常规MAU图谱桨水动力性能预报的数学模型,并对其进行了数值分析。
短句来源
     Prediction of Unsteady Cavitation Performance of Propeller by Lifting-Surface Theory
     升力面理论预报螺旋桨非定常空泡性能
短句来源
     The lifting-line and lifting-surface design method , the harmonic analysis method based on the panel method, new section design ways, the effective operating curves are integrated into a whole design system of the unsteady propeller , the design system is effective and reliable by the design example, the model test and the application to the full scale ship .
     本文把升力线和升力面设计方法、基于面元法预报螺旋桨非定常性能的谐调分析方法,新剖面设计方法、有效运转曲线计算方法组合为一套完整的非均匀流场中螺旋桨设计计算系统,经实例设计和模型试验及实船的应用,该设计系统是可靠且有效的。
短句来源
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  升力面理论
     A refinement in the treatment of boundary value problem of propeller lifting-surface theory
     螺旋桨升力面理论边值问题的精细化处理
短句来源
     Based on the theory of potential flow,steady lifting-surface theory and the potential based low-order surface panel methodi the mathematical models for predicting the performance of the HD propeller and MAU propeller are respectively established in this paper,and the numerical calculations are alsocarried out.
     本文首先基于势流理论和定常螺旋桨的升力面理论,以及基于速度势的低阶面元法理论建立了沪东型(HD)螺旋桨和常规MAU图谱桨水动力性能预报的数学模型,并对其进行了数值分析。
短句来源
     Prediction of Unsteady Cavitation Performance of Propeller by Lifting-Surface Theory
     升力面理论预报螺旋桨非定常空泡性能
短句来源
     As the popular method for the calculation of marine hydrodynamics, the surface panel method has the advantage over the lifting-surface method in the mechanics model and the prediction of pressure distribution, but for the total force of propeller, they have the same computational accuracy.
     面元法作为目前流行的船舶流体力学计算方法,其力学模型较升力面理论更为完善,压力分布的预报计算也优于后者,但就螺旋桨合力的计算而言,两者基本具有同样的计算精度。
短句来源
     This paper has adopted the lifting-surface method for the prediction of unsteady hydrodynamic performance and cavitation performance of propeller.
     本文采用升力面理论预报螺旋桨非定常水动力性能及空泡性能。
短句来源
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  “lifting-surface”译为未确定词的双语例句
     OPTIMUM DESIGN OF A LIFTING-SURFACE STRUCTURE WITH MULTIPLE CONTRAINTS BY INTUITIVE OPTIMALITY CRITERIA
     用直观准则法的飞机翼面结构多约束优化计算
短句来源
     Propeller Analysis and-Design Methods by Numerical Lifting-Surface Theory
     螺旋桨性能计算及设计的升力面方法
短句来源
     A Prediction of Unsteady Propeller Performance with Numerical Lifting-surface Theory
     螺旋桨非定常性能计算的升力面方法
短句来源
     A NEW METHOD FOR SUBSONIC LIFTING-SURFACE THEORY Chinese Helicopter Research and Development Institute
     亚音速升力面理论的一种新解法
短句来源
     AERODYNAMIC SENSITIVITIES FOR SUBSONIC LIFTING-SURFACE
     亚音速升力面气动敏感性导数计算
短句来源
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  lifting-surface
Results are shown for two simple planforms, using inputs from three-dimensional lifting-surface theory and from slender-body theory.
      
The analysis is based on the assumption that the spanwise load distribution is elliptical, and it follows that the two-dimensional lifting-surface integral equation can be reduced to a one-dimensional integral equation of the Wiener-Hopf form.
      
The extremal of the functional satisfy the hull boundary integral equation in a similar way to that of lifting-surface theory and the elevated water surface condition along the spray root line.
      
The airplane arrangements investigated were constructed by disposition of wings in tandem at definite values of the aerodynamic lift and the lifting-surface area.
      


The lift of a shallowly submerged rectangular hydrofoil is discussed in the paper.If the lift coefficient of airfoil is known as C_(L∞),then the lift coefficient of hydrofoil will be C_L=KC_(L∞).With a view to simplify the calculation,the method for calculating K is only discussed among calculation methods.Using this simple method in calculation and analysis,it is shown that the effect of gravity may be neglected under high speed condition,and both the chord length and the thickness of hydro- foil are factors...

The lift of a shallowly submerged rectangular hydrofoil is discussed in the paper.If the lift coefficient of airfoil is known as C_(L∞),then the lift coefficient of hydrofoil will be C_L=KC_(L∞).With a view to simplify the calculation,the method for calculating K is only discussed among calculation methods.Using this simple method in calculation and analysis,it is shown that the effect of gravity may be neglected under high speed condition,and both the chord length and the thickness of hydro- foil are factors to be considered.Then a method for calculating the lift of a shallowly submerged hydrofoil is obtained.The main assumption in deriving formula is as following:(1)The contribu- tion of upper and lower surface of hydrofoil to lift can be studied respectively.The contribution of upper surface to lift is influenced by free surface,while the contribution of lower surface to lift is not influenced by free surface.(2)The effect of gravity may be neglected when speed of hydro- foil is extremely high.The method of lifting surface is adopted in calculating free surface correc- tion factor K of upper surface.Having first confirmed in calculation that the π pattern chordwise vortex distribution has no contribution to K,it is only necessary to set up four π pattern vortices over chordwise in order to calculate K of upper surface of hydrofoil.Four projects were made to carry out tests on lift of hydrofoil of circular-back section. The results show that under shallowly submerged condition,the angle of attack at zero lift varies considerably with submergence.Then a method of correction for aspect ratio of hydrofoil is obtained.After correction of aspect ratio for test results,the nomogram for calculating the lift coefficient of rectangular hydrofoil of circular-back section of 0.06 and 0.1 relative thickness is made out.The result of these two hydro- foil thickness can also be used to calculate the lift of other hydrofoil thickness.

本文讨论浅浸矩形水翼升力的问题。如果已知机翼的升力系数 C_(L∞),则水翼的升力系数 C_L=KC_(L∞)。为了简化计算在计算方法中只讨论计算 K 的方法。文中首先用已有的简单方法进行了计算分析。结果表明在速度较高时可以忽略重力的影响,在浅浸深时弦长与翼厚都是必须考虑的因素。其次导出了浅浸矩形水翼升力的计算方法。导出公式的主要假定是(1)水翼上下表面对升力的贡献可以分别考虑。水翼上表面对升力的贡献受自由面影响,下表面对升力的贡献不受自由面影响。(2)水翼运动速度投高可以忽略重力的影响。在计算上表面的自由面修正因子 K 时,采用升力面方法。计算时首先论证了Π形涡沿展向分布对 K 没有贡献,在弦向只须布置四个Π形涡就足够。所以用布置在弦向的四个Π形涡来计算水翼上表面的 K。最后进行了相对厚度=0.1,展弦比 AR=6,10;=0.06,AR=4,6等四个方案圆背形剖面矩形水翼的升力试验。试验结果表明在浅浸深时零升力角随浸深有很大改变,并导出了水翼展弦比的修正方法。把试验结果经展弦比修正后制成计算=0.1与=0.06圆背形矩形水翼升力系数的诺莫图。计算其它厚度水翼的升力,可用上述二厚度水翼的结果线性插入。

The hydrodynamic characteristics of finite thin wing having uniform motion and with the distance from the wing to a boundary (ground or free surface) changing with the time have been studied. Within the limits of linearized theory, the problem was reduced to a Fredholm singular integral equation of the first kind. The Woodward's method of numerical calculation is extended for solving the integral equation presented here. Calculation results show that the unsteady motion has pronounced influences on the hydrodynamic...

The hydrodynamic characteristics of finite thin wing having uniform motion and with the distance from the wing to a boundary (ground or free surface) changing with the time have been studied. Within the limits of linearized theory, the problem was reduced to a Fredholm singular integral equation of the first kind. The Woodward's method of numerical calculation is extended for solving the integral equation presented here. Calculation results show that the unsteady motion has pronounced influences on the hydrodynamic characteristics of the lifting surface, a phenomenon deserving due consideration in applied engineering.

本文研究以等速运动但距界面(固壁或自由面)的距离随时间变化的有限翼展薄翼的流体动力特性。在线性理论范围内此问题可化成Fredholm第一类奇异积分方程。同时推广了Woodward方法,求其数值解。计算结果表明,运动的非定常性对升力面的流体动力特性具有显著的影响,工程应用中对此需要加以考虑。

On the basis of the method of matched outer and inner asymptotic expansions,the sideslip aerodynamic characteristics of a subsonic airplane are calculated.The body is replaced with source and doublet distributions and the lifting surfaces are replaced with vertex-lattice distributions.A small perturbation mothod is presented for treating the interference problems of a wing-body combination and a wing-body-tail combination.Some concrete examples given at the end of this paper show that the method presented in...

On the basis of the method of matched outer and inner asymptotic expansions,the sideslip aerodynamic characteristics of a subsonic airplane are calculated.The body is replaced with source and doublet distributions and the lifting surfaces are replaced with vertex-lattice distributions.A small perturbation mothod is presented for treating the interference problems of a wing-body combination and a wing-body-tail combination.Some concrete examples given at the end of this paper show that the method presented in this paper is available.

本文根据小扰动渐近展开的内外解衔接法,对亚音速全机侧滑问题,用源(汇)、偶极子分布代表机身,涡格分布代表升力面;並对翼-身、翼-尾干扰提出了小扰动处理法。通过算例表明,本文提供的方法是可行的。

 
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