改装双三角翼对歼击机升阻特性的影响

本文通过理论分析和风洞试验，研究改装双三角翼对飞机动性能的影响。所得结果对飞机设计，特别是改型设计有一定实用价值。     

Constraints on Coronal Outflow Velocities Derived from UVCS Doppler Dimming Measurements and in-Situ Charge State Data

We constrain coronal outflow velocity solutions, resolved along the line-of-sight, by using Doppler dimming models of H I Lyman alpha and O VI 1032/1037 Å emissivities obtained with data from the Ultraviolet Coronagraph Spectrometer (UVCS) on SOHO. The local emissivities, from heliocentric heights of 1.5 to 3.0 solar radii, were determined from 3-D reconstructions of line-of-sight intensities obtained during the first Whole Sun Month Campaign (10 August to 8 September 1996). The models use electron densities derived from polarized brightness measurements made with the visible light coronagraphs on UVCS and LASCO, supplemented with data from Mark III at NCAR/MLSO. Electron temperature profiles are derived from 'freezing-in' temperatures obtained from an analysis of charge state data from SWICS/Ulysses. The work concentrates on neutral hydrogen outflow velocities which depend on modeling the absolute coronal H I Lyα emissivities. We use an iterative method to determine the neutral hydrogen outflow velocity with consistent values for the electron temperatures derived from a freezing-in model.     

脉冲风洞中新型自由天平探索

为解决常规天平在高焓高超声速脉冲风洞中测得信号无法识别、无法提取的问题,提出了一种全新的自由型天平,并设计了两种不同方案(分自由度自由型三分力天平和整体自由型三分力天平)。实验表明这种加速度测力是可行的,并能很好地解决传统天平遇到的问题。     

Mars Global Surveyor Measurements of the Martian Solar Wind Interaction

The solar wind at Mars interacts with the extended atmosphere and small-scale crustal magnetic fields. This interaction shares elements with a variety of solar system bodies, and has direct bearing on studies of the long-term evolution of the Martian atmosphere, the structure of the upper atmosphere, and fundamental plasma processes. The magnetometer (MAG) and electron reflectometer (ER) on Mars Global Surveyor (MGS) continue to make many contributions toward understanding the plasma environment, thanks in large part to a spacecraft orbit that had low periapsis, had good coverage of the interaction region, and has been long-lived in its mapping orbit. The crustal magnetic fields discovered using MGS data perturb plasma boundaries on timescales associated with Mars' rotation and enable a complex magnetic field topology near the planet. Every portion of the plasma environment has been sampled by MGS, confirming previous measurements and making new discoveries in each region. The entire system is highly variable, and responds to changes in solar EUV flux, upstream pressure, IMF direction, and the orientation of Mars with respect to the Sun and solar wind flow. New insights from MGS should come from future analysis of new and existing data, as well as multi-spacecraft observations.     

Modeling of the Magnetospheric Response to the Dynamic Solar Wind

We discuss quasi-static and dynamic models of the magnetotail response to perturbations imposed by the solar wind, focusing particularly on the formation of thin current sheets, their structure and breakup.     

带减阻杆高超声速飞行器外形气动特性研究

采用高超声速风洞测力试验方法测量钝头飞行器头部减阻杆的高超声速气动特性,研究减阻杆的气动减阻原理,分析了多组不同构型减阻杆的减阻效果。结果表明,减阻杆显著减少了钝头飞行器高超声速的阻力,最大的减阻率达到60％之多;减阻效果与减阻杆构型和迎角状态密切相关;减阻杆会诱发稳定性、“热斑”以及非定常脉动等不利问题。     

栅格舵气动与操纵特性高速风洞试验技术研究

为研究飞行器单独栅格舵全尺寸模型气动特性,考核、验证舵控系统操纵性能,在FL-24风洞（1．2m×1．2m）开展了专项试验技术研究。首次在国内高速风洞建立了全尺寸栅格舵高速风洞试验平台,主要内容包括：风洞大载荷侧壁支撑装置设计、高速风洞模型保护装置设计、高灵敏度气动测试天平研制、模型风载条件下变形测试系统设计以及动态气动力测量与数据处理方法等。该项试验技术实现了模型气动与舵控系统以及气动与结构一体化试验验证,为栅格舵尾翼布局飞行器相关专业设计及飞行试验提供了重要试验数据。     

风洞试验模型技术新发展

风洞模型试验是航空航天飞行器研制的重要环节之一。试验模型的设计制造关系到风洞试验的数据质量、效率、周期和成本。本文归纳了近年来国外风洞模型技术的最新发展,分析了快速成型技术在风洞试验模型制造中的发展和应用;阐述了欧、美遥控风洞模型技术的发展理念、关键技术和应用研究;概述了风洞试验模型采用的新材料、抑振和变形测量技术。     

MDOE风洞试验方法研究

在介绍OFAT风洞试验方法和MDOE风洞试验方法概念的基础上,探讨研究了两种试验方法理念的本质区别;简述了MDOE风洞试验方法具体实施的三个过程;归纳分析了MDOE风洞试验方法的应用实例、效能评估和发展前景;意在为国内风洞试验领域科研人员拓展思路、创新方法提供参考。     

大厚度钝后缘翼型气动性能计算研究

大厚度钝后缘翼型由于其气动和结构的优点,近来被作为大型风力机叶片设计时的内侧翼型成为风力机翼型设计的热点之一EULL由于此类翼型厚度和风洞阻塞度的限制,大雷诺数的风洞实验数据很少。耦合RANS方程和基于线性稳定性分析EULL捩预测方法,进行了大厚度钝后缘翼型气动性能计算研究。使用Gridgen程序生成计算网格,湍流模型为S-A模型。对常用的钝后缘修形方式如直接截断、对称增加厚度等并且有风洞实验结果的几种翼型进行了CFD计算并和实验结果及文献计算结果进行了比较。结果表明升力系数在线性段,计算结果和实验结果吻合很好,但是对失速迎角的捕捉能力差;阻力系数计算结果和实验值吻合较好。不同修形方式的计算结果为钝后缘修形设计提供了参考。