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sweepback angle
相关语句
  后掠角
     For the former one,the design philosophy of large sweepback angle of plow blade is introduced and for the latter one,the selection of earth entry angle and the parameters of the curvature of the plow arc discussed in this paper.
     本文对前者提出了大后掠角犁翼设计思想,对后者则讨论了犁刀曲面各参数及入土角的选择。
短句来源
  “sweepback angle”译为未确定词的双语例句
     When the curvature on surface of otter board is 14%, the dihedral angle of the optimal match was 12°, aspect ratio was 1.60 and sweepback angle was 10°.
     当网板的板面曲率为14%、板面折角为12°、展弦比为1.60、后退角为10°时,网板具有较高的水动力性能。
短句来源
     This paper describes a flow visualization experiment over the leeside of a slender tapered wing with a leading edge sweepback angle of 65° and a biconvex section.
     给出了前缘后掠65°、双弧形剖面的细长梯形翼背风面流动显示结果。
短句来源
     The test results indicated as follows: 1. one of the most important factors to influence the hydrodynamic characteristics of otter board was dihedral angle, followed by aspect ratio and sweepback angle.
     试验结果证明影响网板水动力性能的最重要的因素是网板板面折角,其次是展弦比和后退角。
短句来源
  相似匹配句对
     angle.
     角。
短句来源
     ANGLE Program
     ANGLE程序
短句来源
     Analytical and Experimental Study on Limit Cycle Flutter for Sweepback Wing Store
     带外挂后掠机翼极限环颤振的分析与实验研究
短句来源
     Calculation of thickness wave drag coefficient for hypervelocity sweepback space debris
     超高速后掠飞片的厚度波阻系数计算
短句来源
     Design and Wind Tunnel Experimental Investigation of Middling Sweepback Wing Plane Parameter
     中等后掠机翼平面参数设计与实验研究
短句来源
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  sweepback angle
Influence of the sweepback angle and the unit reynolds number on boundary-layer transition at supersonic velocities
      
Detailed heat transfer and pressure distributions were measured at fin deflection angles of up to 30° for a sweepback angle of 67.6°.
      


In this paper, the blunt leading-edge of a wing is taken as mesh points, and there the exact velocity potential equation with central difference scheme and the exact boundary condition are used, while in the other places, the approximate velocity potential equation, which assumes small perturbation in the transverse plane but allows large perturbation in the longitudinal direction, and the corresponding boundary condition are employed. Two numerical examples are following:(1) A rectangular wing having airfoil...

In this paper, the blunt leading-edge of a wing is taken as mesh points, and there the exact velocity potential equation with central difference scheme and the exact boundary condition are used, while in the other places, the approximate velocity potential equation, which assumes small perturbation in the transverse plane but allows large perturbation in the longitudinal direction, and the corresponding boundary condition are employed. Two numerical examples are following:(1) A rectangular wing having airfoil NACA0012, aspect ratio λ = 12, angle of attack α=2°, free stream Mach number M∞ = 0.63. The computed pressure distribution of the root section agrees with the exact numerical subsonic solution given by Sells (1968).( 2 ) The sweepback wing tested by NACA RM A51G31 having airfoil NA-CA64A010 which is perpendicular to 1/4 chord line with sweepback angle X1/4 = 45°, λ = 3 and taper ratio η = 2 ,α=2°, M∞=0.4, 0.8 and 0.9. The computed pressure distributions agree well with those obtained by tests.Under the assumption of local linearization, the stability of the difference equation in line relaxation with Seidel iteration is studied by the von Neumann method and the convergence of the solution of the differential equation equivalent to the above difference equation to the solution of the original differen- tial equation is discussed by the method of separation of variables.The following conclusions are obtained:( 1 ) The stability condition for the line relaxation with Seidel iteration is 0<ω≤2 at locally subsonic points, where ω is the relaxation factor.( 2 ) At locally supersonic points, the relaxation is always unstable. The convergence conditions are as follows. Let the steps Δx (chordwise) and Δz (spanwise) perpendicular to the relaxation line.(3) 0<ω<2, at locally subsonic points.(4) 0 <ω<1+ , at locally supersonic points.The numerical experiences agree with the conclusions ( 1 ), ( 3 ) and ( 4 ), but do not agree with the conclusion ( 2 ).

本文在机翼钝前缘处用精确速势方程和精确的边界条件,其他地方用纵向大扰动而横向小扰动的速势方程和相应的边界条件,联立求解。数值算例1为矩形机翼,展弦比λ=12,翼剖面为NACA0012,自由流的马赫数M_∞=0.63,迎角α=2°,翼根剖面压力分布的计算结果与二元亚音速精确数值解(Sells,1968)接近。算例2为NACA RM A51G31实验的机翼,垂直于1/4弦线的翼剖面为NACA64A010,其后退角χ_(1/4)=45°,λ=3,根梢比η=2,M_∞=0.4,0.8,0.9,α=2°。计算与实验接近。 本文建立跨音速定常小扰动速势差分方程的线松弛改进迭代在局部线化假设下的稳定性条件和松弛解收敛到原来的微分方程解的条件。这些条件大多数与数值实验相符。

The paper concerns separated flow patterns of delta wings and its boundaries, topological analysis of separated flows and vortex flows, vortex breakdown, as well as controlled separation and vortex interaction.Flow patterns about upper and lower surfaces of a series of delta plate wings with sharpened leading-edge sweepback of 15 to 85 deg. at angles of attack up to 90 deg. at low speeds are given. There are nine types of leading-edge separated flows about upper surface; bubble, bubble vortex, streamwise vortex,...

The paper concerns separated flow patterns of delta wings and its boundaries, topological analysis of separated flows and vortex flows, vortex breakdown, as well as controlled separation and vortex interaction.Flow patterns about upper and lower surfaces of a series of delta plate wings with sharpened leading-edge sweepback of 15 to 85 deg. at angles of attack up to 90 deg. at low speeds are given. There are nine types of leading-edge separated flows about upper surface; bubble, bubble vortex, streamwise vortex, concentrated stable vortex, bursting vortex, spiral flow, reversed flow, completely separated flow and asymmetric vortex. Boundary diagrams of the separated flows in the angle of attack versus leading-edge sweepback angle plane are discussed.Qualitative theory of differential equations and topology are very useful in analysing three -dimensional flows and vortex flows. Local properties near singular points, global properties and topological rules of differences between the numbers of. nodal and saddle points, as well as the evolution of the topological structures as a function of parameters have been investigated by previous authors. Now concentrated vortex of a slender wing and spiral flow of a moderate sweepback cropped delta wing are studied.Vortex breakdown usually arises in either of two predominant forms, bubble-like and spiral, and the bursting vortex flow-fields of the two-forms are described, moreover, sub-species are mentioned. The Position of vortex bursting point can be determined by jet-like distribution of axial velocity in front of it and wake-like one behind it. Theories of vortex breakdown and theoretical methods to evaluate the position of vortex bursting point are stated. Upstream movement of the bursting point of a: strake-wing is different from that of a very slender wing.Concept of controlled separation in three-dimensional flows is very important in air vehicle configuration design. The types of unstable separated flows about wings and the stability of vortex flows can be controlled by a concentrated stable vortex. The effect of strake vortex on wing vortex is studied. Displacement, coiling or merging may appear due to interaction between two stable vortices rotating in same direction. The merging of two vortices of a double delta wing and that of spanwise blowing on a wing are shown.

本文简要介绍研究旋涡运动在以下问题上的某些结果:低速不同后掠角三角翼在各个迎角下的九种分离流类型及其边界;应用微分方程定性论与拓扑学对三维分离流与旋涡流的分析;旋涡破裂形态,对三角翼前缘涡破裂的实验研究与理论分析;受控分离与旋涡的干扰,二旋涡的位移、绕转与合并等。

This paper uses the three-dimensional waving plate model and optimummotion theory to analyse lunate-tail swimming propulsion, and so a comparatively systmatic study of the three classes of fish propulsive modes has been carried out. Theoretical results show that lunate-tail, with high-aspect-ratio, spanwise tapering tip and moderate sweepback angle, of many fast-swimming ocean animals, may gain the nearly best propulsive characteristics. Estimation of a porpoise swimming performance gives satisfactory...

This paper uses the three-dimensional waving plate model and optimummotion theory to analyse lunate-tail swimming propulsion, and so a comparatively systmatic study of the three classes of fish propulsive modes has been carried out. Theoretical results show that lunate-tail, with high-aspect-ratio, spanwise tapering tip and moderate sweepback angle, of many fast-swimming ocean animals, may gain the nearly best propulsive characteristics. Estimation of a porpoise swimming performance gives satisfactory results.

本文运用三维波动柔板位流模型与最佳游动方式理论,继续分析了新月形鱼尾的推进性能,从而实现了对鱼类三种主要推进模式的较为系统的研究。理论分析表明,高速海洋动物所具有的大展弦比、尖叶梢、中等后掠的新月形尾能获得接近于最佳的推进性能。对海豚游动特性的理论估算也给出了令人满意的结果。

 
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