摘要
为了在低速风洞中研究推进系统进气和喷流对战斗机气动特性的影响，发展了采用模拟器进行战斗机模型试验的新技术，研制了能够模拟发动机进排气的引射式模拟器，并进行了模拟器的校准。为了验证该项试验技术，研制了简化的战斗机试验模型和模型支撑装置，在中国空气动力研究与发展中心Ф3．2m低速风洞进行了测力试验，试验的迎角范围-5°～48°，侧滑角范围0°～15°，试验风速为70m／s。试验结果表明：试验能够较真实地模拟战斗机发动机的进气和喷流情况，进气流量可模拟到90％以上，喷流的最高落压比可达到2．95。该项试验技术为开展进气／喷流对战斗机的气动特性的影响研究提供了新的技术途径。
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 Ф3.2m 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.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2011年第3期46-49,共4页
Journal of Experiments in Fluid Mechanics
