实验流体力学2011，Vol.25Issue(3)：46-49,4.
战斗机推进系统模拟低速风洞试验技术研究
Investigation on test technique of fighters with propulsion simulation in a low speed wind tunnel
王勋年 1巫朝君 2陈洪 2李真旭2
作者信息
- 1. 西北工业大学航空学院,西安710072
- 2. 中国空气动力研究与发展中心,四川绵阳622662
- 折叠
摘要
Abstract
In order to investigate the impact of intake and jet produced by propulsion systems on the aerodynamic characteristics of fighters in low speed wind tunnels, we developed a new test technology for a fighter model with ejection simulator. After the ejection simulator was produced, the simulator was calibrated. In order to validate the test technology, a reduced fighter model and its support was designed and manufactured. The test of force measurement on the fighter model with the simulator was carried out in the Φ3.2m low speed wind tunnel of CARDC.The test air speed is 70m/s, the AOA range -5°～48°and the sideslip angles range 0°～15°. The test results are as follows: the test technology can simulate the effect of intake and jet of fighter propulsion system, 90 percent of intake flux can be simulated, and the maximum pressure ratio of jet reaches 2.95. The test technology is a new way to research the effect of intake and jet on aerodynamic characteristics of fighters.关键词
战斗机/发动机/推进系统/模拟器/试验技术Key words
fighter/ engine/ propulsion system/ simulator/ test technology分类
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王勋年,巫朝君,陈洪,李真旭..战斗机推进系统模拟低速风洞试验技术研究[J].实验流体力学,2011,25(3):46-49,4.
