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 风洞实验 在 航空航天科学与工程 分类中 的翻译结果: 查询用时：0.079秒
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 风洞实验
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 wind tunnel test
 An experimental investigation of the static pressure fluctuation generation mechanism was performed for different transonic wind tunnel test section perforated wall configurations. An application in a small-scale wind tunnel test is shown, demonstrating mapping of pressure data to the three-dimensional model surface. A variable speed, seamless belt formed the wind tunnel test section wall. The above algorithms were used to analyze the NACA0012 wind tunnel test data at flow conditions of the velocity 40?m/s and AOA 16°. Next, effectiveness of the concept in reducing drag of bluff bodies such as a two-dimensional flat plate at large angles of attack, rectangular prisms and three-dimensional models of trucks is assessed through an extensive wind tunnel test-programme. 更多
 wind tunnel experiment
 This equation reveals ripple structures which then undergo a coarsening process, as observed in wind tunnel experiment. The analysis is performed for three different data sets obtained from a wind tunnel experiment, a free-jet experiment and an atmospheric boundary layer experiment with Taylor-Reynolds numbers $R_{\lambda} = 80,190,17000$, respectively. Wind tunnel experiment of drag of isolated tree models in surface boundary layer Wind flow and wind loads on the surface of a towershaped building: Numerical simulations and wind tunnel experiment Soil erodibility can be evaluated by measuring soil physiochemical properties, scouring experiment, simulated rainfall experiment, plot experiment and wind tunnel experiment. 更多
 wind tunnel tests
 Wind tunnel tests indicate that the critical movement velocity of shell is lower than that of quartz sand of the same grain size. A frequency domain method for estimating wind-induced fluctuating internal pressure of structure with single windward opening is presented in this paper and wind tunnel tests were carried out to verify the theory. A series of low-rise building models with various openings and internal volumes were designed for wind tunnel tests with results agreeing well with analytical results. Theoretical analysis and wind tunnel tests were carried out to study wind-induced internal pressure response for the structure with single windward opening and background leakage. A series of models for low-rise building with various opening ratios and background leakage were designed and wind tunnel tests were conducted. 更多
 wind tunnel testing
 Then, the idea of producing computer animations to represent the aeroelastic deformation of bridges simulating virtual boundary layer wind tunnel testing is presented showing pictures of the Tacoma Narrows and Messina Bridges. Theoretical and experimental investigations of wall adaptation control in wind tunnel and hybrid wind tunnel testing Dual hologram shearing interference technique with enhanced sensitivity for wind tunnel testing Finally, the design success is verified by wind tunnel testing. Aeroelastic wind tunnel testing of the laminate was performed and the result showed that flutter, a dynamic instability occurred. 更多
其他
 The paper makes an analysis of the results of wind Tunnel tests on the ball model with hollow base. It is apparent obviolls that the ball with bollow base with holes around its side wall has a favourable effect on the characteristic of drags. The results of the base drag is especially apparent in our NH-1 wind tunnel. The optimum porosity ratio is about 35%. This method will be expected to have similar satisfactory result, if it is extended to a second age ball with hollow base. 本文给出了底凹弹丸模型风洞实验结果的分析。从中可见,绕尾部带有导气孔的底凹弹丸具有令人满意的阻力特性,在NH-1风洞试验中,底部阻力的影响特別明显.最佳开孔比约为35％。若把此方法推广到第二代底凹弹丸中,将同样有效。 The Northwestern Polytechnical University 10 by 30 cm. transonic airfoil wind tunnel was converted from the 30 by 30 cm. supersonic wind tunnel in 1976. This facility is a two-dimensional tunnel with parallel sidewalls and top and bottom slotted walls which operates on direct blowdown from a supply of dry air. On each sidewall, there is a turnable disk at the region occupied by the model. Various open-area-ratios may be obtained by sealing some slots of the slotted walls. The tunnel is capable of operating at... The Northwestern Polytechnical University 10 by 30 cm. transonic airfoil wind tunnel was converted from the 30 by 30 cm. supersonic wind tunnel in 1976. This facility is a two-dimensional tunnel with parallel sidewalls and top and bottom slotted walls which operates on direct blowdown from a supply of dry air. On each sidewall, there is a turnable disk at the region occupied by the model. Various open-area-ratios may be obtained by sealing some slots of the slotted walls. The tunnel is capable of operating at Mach number from 0.4 to 1.0 with corresponding Reynolds number range of 3×106 to 6×106 based on a 10 cm chord. Empty tunnel calibrations show that the local Mach number distribution obtained from wall static pressure varies less than ±0.005 from the average value in the test region occupied by the model.Surface pressure distributions on three RAE-104 section models with 5 cm., 10 cm. and 12.5 cm. chords respectively were measured in conditions of zero angle of attack: the Mach number range of about 0.4 to 0.8 and several open-area-ratios. Results of measurements show that when the value of open-area-ratio is 0.02 and the corresponding wind tunnel parameter T equals 0.64, the blockage interference practically vanishes.Comparisons between surface pressure distributions of RAE-104 section models which were obtained under three conditions of sidewalls show that;1.The lift coefficients obtained under conditions of porous turnable disk without local sidewall suction are much less than those obtained under conditions of free interference.2.The lift coefficients obtained under conditions of the solid turnable disk closely approach those under conditions of free interference, when the Mach number is less than 0.7.3.It is found that under the conditions of larger Mach numbers and angles of attack the turnable disk with local sidewall suction is the best one in the three.The comparison between results in this facility and those in the British National Physical Laboratory 20 by 8 inch transonic tunnel is presented. 在西北工业大学跨音速翼型风洞(又名57风洞)中,对弦长分别为50、100、125毫米的三个RAE 104翼型模型进行了压力分布测量。结果表明:当上下壁开闭比选用2％时,风洞的堵塞干扰基本消除。 采用实侧壁、多层网板而不进行抽气及多层网板进行抽气这三种侧壁状态,对RAE 104翼型模型所做实验结果表明:有多层网板而不抽气,使升力系数大大低于无干扰值;在M风洞实验结果与英国NPL20英寸×8英寸跨音速风洞实验结果的比较。 Many of the current fighter aircraft use maneuvering flaps to enhance air combat maneuverability. Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality. This study shows that maneuvering flap is an effective... Many of the current fighter aircraft use maneuvering flaps to enhance air combat maneuverability. Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality. This study shows that maneuvering flap is an effective measure to improve air combat capability of fighter aircraft at large angles of attack. Maneuvering flaps can effectively control the flow Separation and decrease the drag at large angles of attack. They also can expand the buffet boundary and decrease the buffet intensity. As a result, the large angle-of-attack flying quality can be significantly improved by utilization of maneuvering flaps. To the end of optimum comprehensive effect, the effects on both the aircraft structure and the system must be taken into account during the choice of the parameters of maneuvering flaps. 机动襟翼是现代战斗机提高机动格斗能力的常用措施。本文根据风洞实验结果,讨论了机动襟翼减阻的能力和原因,襟翼弦长和展长的影响,前缘襟翼和后缘襟翼的配合使用问题,机翼边条和机翼平面形状对机动襟翼减阻的影响,以及机动襟翼对大迎角飞行品质的改善情况。讨论表明,机动襟翼是提高战斗机空战格斗能力的有效措施。它能控制气流分离和减小大迎角时的阻力,提高抖振边界和降低抖振强度,改善大迎角的飞行品质。为了得到最佳的综合效果,机动襟翼的参数选择必须考虑对飞机结构和系统的影响。 << 更多相关文摘
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