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71.
72.
合成射流对失速状态下翼型大分离流动控制的试验研究 总被引:1,自引:0,他引:1
为研究低速状态合成射流在抑制翼型气流分离和推迟失速方面的控制机理, 开展了NACA0021 翼型失速特性射流控制的风洞试验研究. 通过系统性的模型测力、翼型瞬态流场粒子图像测速和边界层速度测定的对比试验, 深入探索了合成射流各参数对翼型失速特性控制效果的影响规律. 试验结果表明射流偏角在翼型升力和失速迎角控制方面的效果对射流动量系数较为敏感: 当动量系数较大时, 近切向射流的控制效果更好. 射流动量系数为0.033 时, 偏角30°的射流使得翼型升力系数峰值提高23.56%, 失速迎角增大5°; 而动量系数较小时, 偏角较大的射流能够获得最佳控制效果. 射流动量系数为0.0026 时, 法向射流对翼型最大升力系数控制效果最好(提高9.2%). 相似文献
73.
The Chinese Area Positioning System (CAPS) is based on communication satellites with integrated capability, which is different
from the Global Positioning System (GPS), the International Maritime Satellite Organization (Inmarsat) and so on. CAPS works
at C-band, and its navigation information is not directly generated from the satellite, but from the master control station
on the ground and transmitted to users via the satellite. The slightly inclined geostationary-satellite orbit (SIGSO) satellites
are adopted in CAPS. All of these increase the difficulty in the design of the system and terminals. In this paper, the authors
study the CAPS configuration parameters of the navigation master control station, information transmission capability, and
the selection of the antenna aperture of the communication center station, as well as the impact of satellite parameters on
the whole communication system from the perspective of the transmission link budget. The conclusion of availability of the
CAPS navigation system is achieved. The results show that the CAPS inbound communication system forms a new low-data-rate
satellite communication system, which can accommodate mass communication terminals with the transmission rate of no more than
1 kbps for every terminal. The communication center station should be configured with a large-aperture antenna (about 10–15
m); spread spectrum communication technology should be used with the spreading gain as high as about 40 dB; reduction of the
satellite transponder gain attenuation is beneficial to improving the signal-to-noise ratio of the system, with the attenuation
value of 0 or 2 dB as the best choice. The fact that the CAPS navigation system has been checked and accepted by the experts
and the operation is stable till now clarifies the rationality of the analysis results. The fact that a variety of experiments
and applications of the satellite communication system designed according to the findings in this paper have been successfully
carried out confirms the correctness of the study results.
Supported by the National Basic Research and Development Program of China (Grant No. 2007CB815504) and the Technology Research
and Development Program of China (Grant No. 2007AA12z343) 相似文献
74.
通过在NF-3低速风洞专门研制的翼型模型及相应的俯仰和沉浮振动机构,选用NACA0012翼型进行大迎角下不同频率的振动实验,研究了模型振动平均状态下对其气动力特性的影响情况,并在N-S方程基础上对振动流场进行了初步分析。实验与计算研究的结果表明:在临近定常失速迎角的大迎角条件下,翼型的振动可以引起旋涡分离,导致翼型升力减小和失速迎角的提前;就所讨论的两种振动模式而言,俯仰振动的影响大于沉浮振动。所以,为了提高飞机模型,尤其是大展弦比飞机模型的风洞实验精准度,在模型设计和加工时要特别注意加强机翼弦向的扭转刚度。 相似文献
75.
76.
肥西地区侏罗纪防虎山组、园筒山组和早白垩世周公山组稀土元素具有如下特征: ∑REE为157 μg·g-1,δEu为0.69,(La/Yb)N为11.1.根据稀土元素比值、方差和以及REE分布模型判断,类似于佛子岭群和卢镇关群,后者可能是前者的主要源岩.三尖铺组和黑石渡组具有高的稀土总量,∑REE为264.8,328.2 μg·g-1,高Eu负异常,δEu为0.57,0.67和低的Eu/Sm比值(0.18~0.19),不同于大别山地区变质岩,其源岩值得进一步研究.正阳关组稀土元素特征类似大别杂岩和卢镇关群,表明大别杂岩在新第三纪遭受剥蚀,和卢镇关群一并成为前者的源岩.淮南地区中生代砂岩具有低的稀土总量,∑REE为80.9 μg·g-1,δEu为0.66,(La/Yb)N为5.7,不同于大别山北缘砂岩以及变质岩,说明其物源不是来自于大别山地区. 相似文献
77.
数值模拟零质量射流与YLSG 107翼型绕流的干扰流场,探讨零质量射流在高升力翼型失速控制中的控制效果、控制特性及控制机理.数值模拟以积分形式雷诺平均Navier-Stokes(N-S)方程为控制方程,采用格心有限体积法进行求解.通过在喷口上施加非定常边界吹/吸边界条件模拟射流对翼型绕流的干扰.采用与风洞实验相同的来流状态和控制参数进行数值模拟,得到与实验相吻合的结果.为进一步研究控制特性和控制规律、提出改进的实验方案,研究不同动量系数、不同射流偏角对控制效果的影响,并对法向射流和近切向射流进行较深入的比较.研究表明,先前的风洞实验对应的射流动量系数(0.000 014)偏小是控制效果不显著的重要原因之一,必须达到0.001以上才有明显控制效果(射流动量系数为0.005时可使该翼型失速迎角增大2°,最大升力提高8.7%);近切向射流在失速控制方面明显优于法向射流. 相似文献
78.
The dynamic stall process in three-dimensional (3D) cases on a rectangular wing undergoing a constant rate ramp-up motion
is introduced to provide a qualitative analysis about the onset and development of the stall phenomenon. Based on the enhanced
understanding of the mechanism of dynamic stalls, a 3D dynamic stall model is constructed with the emphasis of the onset,
the growth, and the convection of the dynamic stall vortex on the 3D wing surface. The results show that this engineering
dynamic stall model can simulate the 3D unsteady aerodynamic performance appropriately. 相似文献
79.
The prediction of the aerodynamic performance of pitching airfoils in stall conditions is considered in the context of strong viscous–inviscid interaction modelling. The aim of the work is to demonstrate the capabilities of a low‐cost dynamic stall model well suited for engineering applications. The model is formulated on the basis of a standard panel method combined with a vortex blob approximation of the wake. The development of the boundary layer over the airfoil and the evolution of the shear layer in the wake are taken into account by means of strong viscous–inviscid interaction coupling. To this end a transpiration layer is added to the inviscid formulation which represents the displacement effect viscosity results in the flow while the non‐linear coupled equations are solved simultaneously. Separation is modelled by introducing a second wake originating from the separation point (‘double‐wake’ concept) which is provided as part of the boundary layer solution. The theoretical presentation of the model is supported with favourable comparisons to four sets of wind tunnel measurements. Copyright © 2007 John Wiley & Sons, Ltd. 相似文献
80.
本文对一高负荷跨音转子采用掠技术进行了改型设计,并通过数值模拟对原型以及前、后掠转子分别进行了流场分析。结果发现掠叶片效率和压比与原型叶片相差不大,但是前掠叶型的失速裕度得到了大幅提高。同时前掠叶型的堵塞流量比原始叶型增大,而后掠叶型却明显减小。叶片采用掠之后一方面前缘位置变化所引起的径向压力输运改变了入口来流条件,另一方面气动掠还直接影响到了叶片吸力面附面层内低能流体的径向输运以及在叶尖区域的集聚,从而使流场内部的激波强度及相对位置明显变化,并最终导致叶片不同叶高载荷分布规律的改变。 相似文献