基于张线尾撑的进气道低速风洞试验技术研究

为了在φ3.2m风洞中开展战斗机大迎角进气道特性试验研究,结合该风洞开口试验段及支撑装置的特点,研制了能够模拟战斗机进气道流量的小型引射器装置,发展了基于引射器/张线尾撑一体化设计的战斗机大迎角进气道试验技术。为了验证该项试验技术,研制了进气道流量测量装置,以及基于数字阀的气源控制系统;进行了装置性能研究,并利用某战斗机模型开展了飞机鸭翼对进气道性能的影响试验研究。研究结果表明：引射器引射流量达1.34kg/s,引射器/张线尾撑一体化方案可完全满足我国已有战斗机在3m量级风洞开展进气道试验的流量模拟及开展大迎角试验研究的需求;鸭翼对战斗机进气道性能影响研究为进气道试验模型外形模拟提供了依据。

The investigation of the inlet test technology based on wire sting support in low speed wind tunnel

In order to investigate the inlet characteristic of the fighter at high attack angle in φ3.2m wind tunnel,considering the specialties of the open test section and the supporting equipment,a small-sized ejector which could simulate the inlet flow of the fighter and the test technology of fighter inlet based on ejector/wire sting support integrated design were developed.Inlet flow measurement equipment and gas source control system based on digital valve were developed to validate the test technology.The performance of the system was studied,and the test investigation of the canard wing influencing the inlet performance for certain fighter was carried out.The results showed that the injected flow mass of the ejector was up to 1.34kg/s,and the ejector/wire sting support integrated design could completely satisfy the flow mass simulation when the inlet test of the fighter was carried out in a 3m order wind tunnel and requirement of high attack of angle test investigation.What＇s more,the investigation of the canard wing influencing the inlet characteristic provided evidence for the simulation of the model shape during the inlet test.