前体非对称涡Re效应初探及其风洞模拟技术

对不同长细比(11和6.15)的细长旋成体模型在低速风洞中完成了亚临界和 临界雷诺数(Re)的测压实验研究.结果表明,只要后体尾部截断至离二涡区足够远,就不会影响由前体二涡主控的多涡系结构,并且头部扰动与非对称涡响应之间的相关关系也保持不变,这为在常规低速风洞中通过增大旋成体直径、减小长细比来扩大Re实验范围提供了实验依据.基于此技术,临界Re下低速实验结果表明细长旋成体在层流和转捩分离区的截面压力分布有明显的区别,导致在临界Re内的侧向力较亚临界显著减小,而且头部扰动对背涡流动的主控作用明显减弱,单孔位微吹气扰动主动控制技术不再适用.      

Schemed Power-augmented Flow for Wing-in-ground Effect Craft in Cruise

To provide detailed insight into schemed power-augmented flow for wing-in-ground effect(WIG) craft in view of the concept of cruising with power assistance,this paper presents a numerical study.The engine installed before the wing for power-augmented flow is replaced by a simplified engine model in the simulations,and is considered to be equipped with a thrust vector nozzle.Flow features with different deflected nozzle angles are studied.Comparisons are made on aerodynamics to evaluate performance of power-augmented ram(PAR) modes in cruise.Considerable schemes of power-augmented flow in cruise are described.The air blown from the PAR engine accelerates the flow around wing and a high-speed attached flow near the trailing edge is recorded for certain deflected nozzle angles.This effect takes place and therefore the separation is prevented not only at the trailing edge but also on the whole upper side.The realization of suction varies with PAR modes.It is also found that scheme of blowing air under the wing for PAR engine is aerodynamically not efficient in cruise.The power-augmented flow is extremely complicated.The numerical results give clear depiction of the flow.Optimal scheme of power-augmented flow with respect to the craft in cruise depends on the specific engines and the flight regimes.     

计算空气动力学的流场和图形显示技术

本文阐述了计算空气动力学流场和图形显示的重要性,它的基本方法和主要内容;介绍了在VAX计算机上研制的计算空气动力学流场和图形显示软件的主要功能。     

单片机及多种流量计在伺服阀气动配磨中的应用

介绍了一台三种形式流量计可任选并由单片机对测试过程进行控制,采样,计算并打印输出滑阀副搭接量值的试验设备。     

战斗机推力矢量关键技术及应用展望

战斗机推力矢量技术可极大地扩展战斗机使用包线,提升飞行安全性,增强飞机作战能力,是航空领域的重要关键技术,是先进战斗机的典型标志之一。该技术涉及气动、进排气、发动机和飞行控制等多个领域,其综合实现是一项跨领域、紧耦合、高风险的系统工程。本文回顾了战斗机推力矢量技术的发展历程,分析了关键技术体系,结合中国首架轴对称推力矢量验证机的工程实践,阐述了大迎角内外流气动设计、推力矢量发动机、综合飞/发控制和战斗机过失速机动飞行验证等关键技术,展望了推力矢量技术对作战效能的贡献及未来的应用方向。     

提高航空发动机性能的弯扭导向器技术

给出了采用弯扭导向器提高发动机性能的设计原则：在全三维弯扭设计时，必须在保证涡轮前总温、总压和燃气流量的前提下，合理调整尾喷管面积，提高涡轮后背压，保证在设计转速下涡轮输出功与原型涡轮级相同，从而保证了压气机的设计点和喘振裕度，同时提高了发动机推力、降低油耗。     

Numerical analysis on noise of rotor with unconventional blade tips based on CFD/Kirchhoff method

A solver is developed aiming at efficiently predicting rotor noise in hover and forward flight. In this solver, the nonlinear near-field solutions are calculated by a hybrid approach which includes the Navier-Stokes and Euler equations based on a moving-embedded grid system and adaptive grid methodology. A combination of the third-order upwind scheme and flux-difference splitting scheme, instead of the second-order center-difference scheme which may cause larger wake dissipation, has been employed in the present computational fluid dynamics (CFD) method. The sound pressure data in the near field can be calculated directly by solving the Navier-Stokes equations, and the sound propagation can be predicted by the Kirchhoff method. A harmonic expansion approach is presented for rotor far-field noise prediction, which gives an analytical expression for the integral function in the Kirchhoff formula. As a result, the interpolation process is simplified and the efficiency and accuracy of the interpolation are improved. Then, the high-speed impulsive (HIS) noise of a helicopter rotor at different tip Mach numbers and on different observers is calculated and analyzed in hover and forward flight, which shows a highly directional characteristic of the rotor HIS noise with a maximum value in the rotor plane, and the HSI noise weakens rapidly with the increasing of the directivity angle. In order to investigate the effects of the rotor blade-tip shape on its aeroacoustic characteristics, four kinds of blade tips are designed and their noise characteristics have been simulated. At last, a new unconventional CLOR-II blade tip has been designed, and the noise characteristics of the presented CLOR-II model rotor have been simulated and measured compared to the reference rotors with a rectangular or swept-back platform blade tip. The results demonstrate that the unconventional CLOR-II blade tip can significantly reduce the HSI noise of a rotor.     

某涡轮级三维流场非定常数值研究

基于耦合Lantry-Menter转捩模型的SST(Shear stress transport)湍流模型,对某涡轮级在3个雷诺数工况下的全三维流场分别进行了定常、非定常数值模拟,目的在于对比分析两种计算方法所得结果之间的差异。计算结果表明,进口雷诺数为4×104时和5×105时,定常与非定常计算的涡轮级效率的差异较大,最大相差0.6个百分点,而当雷诺数为8×104时,两者差异很小;非定常计算能够较好的模拟叶尖泄漏涡的发展过程、低雷诺数下上游尾迹与下游转子叶片吸力面分离边界层干涉诱导卷起涡的形成、输运及其所导致的叶片吸力面表面压力大幅波动等非定常流动现象。最后,给出了转子出口截面上周向与径向的非定常压力脉动的分布,为基于Lighthill声类比方法的计算气动声学研究奠定了基础。     

返回器稀薄区气动特性工程计算方法的应用研究

中国航天返回器再入过程采用非弹道式再入轨道,其高空稀薄区滞留时间显著增长,稀薄效应对再入飞行的影响显著增强,因此快速而准确地预测返回器稀薄区气动特性变得非常重要。文章分析归纳了多种稀薄区气动特性工程计算方法即桥函数方法的发展和应用,并以 Stardust 返回舱为对象,对比分析了三种不同桥函数的预测精度,给出了在航天返回器气动预测中更为合适的工程方法。结果显示：不同桥函数预测结果差别很大;在不同攻角下,与数值模拟的对比分析表明,局部桥函数方法气动特性预测结果基本优于其它桥函数,尤其是在力矩系数预测上。因此稀薄区气动特性的预测采用局部桥函数较为合适。