This paper briefly presents a method of uncertainty analysis for wind tunnel test data.
本文简要介绍了风洞数据不确定度分析方法。
In this paper, the initial stage in application of fuzzy logic to aircraft high-Angle-of attack aerodynamics using wind tunnel test data is outlined.
本文概述最初阶段利用风洞试验数据应用模糊逻辑研究飞机大攻角空气动力学的情况。
Through analyzing the methods and combination of the low speed wind tunnel test data, the position of the separation point can be detected accurately.
通过对试验结果进行数据处理，验证了该判定方法对分离点位置判定的正确性和有效性。
By means of regression analysis of the wind tunnel test data from 50 model ships, a new method for calculating the wind coefficient of ships has been obtained.
通过对50条船模风压系数的风洞试验数据进行回归分析，得出一种由船型数据来估算风压系数的新方法。
These are compared with simulating plates of target contour, wind tunnel test data, high altitude test data. Good flow field quality is given for the typical engine.
将这些技术参数和图谱与模拟板的目标图谱数据、风洞吹风试验数据及高空台试验推算结果进行了综合分析与对比，较完整地表述了发动机进口的流场品质。
Wind vibration analysis based on numerical simulation mentioned above checked by the results gained time-history analysis based on wind tunnel test data is applied in this paper.
以基于风洞试验风压数据的风振时程分析结果为参考，对基于数值模拟的风荷载时程进行校核并应用于该结构的风振时程分析。
The calculated piston wind velocity accords with the measured result on site through making a comparison with tunnel aerodynamic test data of real vehicles.
以实车的隧道空气动力学试验资料为参照进行对比计算，计算活塞风速度与实测结果较好符合。
The paper deduces the theoretical derivation of figure coefficient of wind load in wing tunnel test, which can do help data processing of wing tunnel test.
较详细的演绎了风洞测压试验中关于风载体型系数的理论推导公式，为风洞试验数据处理提供了帮助。
It is an approximate theoretic method with simular result to the data of wind tunnel test.
该方法是一种近似理论方法，其结果与风洞试验数据很接近。
An aircraft model was tested in the FL-8 low speed wind tunnel. The test data were analyzed.
在FL - 8风洞中采用某型号飞机的动导模型进行了旋转流场下滚转振荡试验研究，对试验数据进行简单分析。
Three types of form-finding are offered. Meanwhile, combined with the data of wind-tunnel test, the working behaviors under different wind loads are compared and analyzed.
并结合风洞试验结果，对三种找形方案，即不采用稳定索、采用交叉稳定索、采用斜稳定索的结构形式在不同工况下的受力性能进行了比较分析。
Based on the analysis of the differences between wind tunnel test and field measurements and the differences between numerical results and test data, some referential conclusions are drawn.
将数值预测的压力场与实测结果及缩尺模型风洞试验数据进行了比较，分析了风洞试验与场地实测之间、数值模拟与试验之间的异同，得到一些有参考价值的结果。
Furthermore, the buffet boundary correlation for the JL-6 aircraft was analyzed using the data obtained from wind tunnel tests and the flight test data of the JL-6 aircraft.
利用风洞试验和飞行试验得到的数据进行了JL - 6飞机抖振边界相关性分析。
Furthermore, the buffet boundary correlation for the JL-6 aircraft was analyzed using the data obtained from wind tunnel tests and the flight test data of the JL-6 aircraft.
利用风洞试验和飞行试验得到的数据进行了JL - 6飞机抖振边界相关性分析。
应用推荐