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91.
为了研究混凝土超高速侵彻效应的相似规律,总结相似关系基本理论并开展1.4~3.9 km/s 的混凝土侵彻实验,综合本文实验和相关文献实验结果确定关键相似准数并得到归一化侵彻深度的变化规律。结果表明,归一化侵彻深度主要取决于Johnson 数、弹靶密度比和弹体长径比,弹靶强度比和弹头形状系数等因素影响不大;归一化侵彻深度随归一化撞击速度增加而先增后减;当撞击速度接近混凝土纵波声速时,存在以侵彻深度突降为主要现象的“跨声速效应”。 相似文献
92.
In this article, the transonic inviscid flow over a deformable airfoil with plunging motion is studied numerically. A finite volume method based on the Roe scheme developed in a generalized coordinate is used along with an arbitrary Lagrangian-Eulerian method and a dynamic mesh algorithm to track the instantaneous position of the airfoil.The effects of different governing parameters such as the phase angle, the deformation amplitude, the initial angle of attack, the flapping frequency, and the Mach number on the unsteady flow field and aerodynamic coefficients are investigated in detail. The results show that maneuverability of the airfoil under various flow conditions is improved by the deformation. In addition, as the oscillation frequency of the airfoil increases, its aerodynamic performance is significantly improved. 相似文献
93.
A parallel algorithm is presented for explicit solution of compressible Euler equations. Upwinded forms of the equations are used in conjunction with the finite element formulation. The solution domain is subdivided into overlapped blocks which are distributed to available workstations. Parallelization is achieved by using a machine portable parallel library. This, together with the usage of an explicit time-integration scheme, makes the implementation of the algorithm on distributed systems a rather straight-forward task. Furthermore, it provides a very flexible platform for load balancing of available computers. 相似文献
94.
1.5级跨音速压气机内部流场数值分析 总被引:1,自引:0,他引:1
本文以正在建设的1.5级跨音压气机试验台所采用的压气机为研究对象,利用NUMECA软件计算了该压气机在不同转速下的特性曲线,并在设计转速下,对其内部流场进行了分析研究.研究表明:激波位置和强度随压气机运行工况的变化而变化;在近失速工况和堵塞工况时,压气机内部流动出现分离;在设计工况时,压气机内部流动状况良好.上述结论,可以为试验台建设中,探头位置的确定和激光测窗位置的选取等提供指导和帮助.此外,该算例作为一盲解,将来同实验结果对比后,可以用来检验和校准CFD程序,为国内F级燃机设计平台的建设打下良好的基础. 相似文献
95.
本文运用赝势函数变分有限元方法数值模拟了绕翼型的跨音速有旋流动。在含有激波的跨音速有旋流动中,势函数已不存在,但为了保留势函数模型在求解方面的优越性,上海大学的刘高联引入了一个通用函数一赝势函数,可以看出该赝势函数保持了势函数的所有好处,又突破了流动有势的限制,是势函数对有旋流动的一个自然的、物理上相容、数学上求解简便的推广,进一步地,刘高联还得到了赝势函数的变分原理族,为变分有限元法求解有旋流动打下了基础。另一方面,为了提高数值求解的收敛性和有效地捕捉流场中的激波,本文还采用了“人工密度”办法。绕翼型的跨音速有旋流动的计算实践证明了赝势函数的有效性。 相似文献
96.
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98.
S. V. Golovin 《Journal of Applied Mechanics and Technical Physics》2003,44(3):344-354
Exact solutions of the Kármán–Guderley equation that describes spatial gas flows in the transonic approximation are considered. A group stratification of the equation with respect to the infinite-dimensional part of the admissible group is constructed. New invariant and partly invariant solutions are obtained. The possibility of existence of solutions continuous in the entire space is analyzed for invariant submodels with one independent variable. A solution of the Kármán–Guderley equation of the double-wave type is constructed. 相似文献
99.
The transonic flowfields and vortex-breakdown over a slender wing with the angle of attack from 10° to 28° are studied numerically,
and the emphasis is on the secondary separation and the charateristics of vortex-breakdown. The results indicated that: (a)
TVD schemes have strong capability for capturing vortices in three-dimensional transonic separated flow at large angle of
attack. (b) The development of secondary vortices is more complex than that of leading-edge ones, and is affected by wing's
configuration, angle of attack and compressibility simultaneously, and the effect of compressibility is more severe at low
angle of attack. (c) The starting angle of attack for vortex-breakdown (when vortex bursting point crosses trailing-edge)
is about 18° forM∞=0.85, then the bursting point moves upstream quickly with increasing angle of attack. (d) At α=24°, breakdown occurs over
most part of upper side, and the wing begins to stall. Therefore, there is a large lag of angle of attack between the beginning
of vortex-breakdown and the stall of the wing. (e) This lag increase with the decreasing of Mach number. 相似文献
100.