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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Φ3.2m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 study the influence of air intake and jet flow on the aerodynamic characteristics of fighter jets in low speed wind tunnels, a new technique for simulating fighter model tests using simulators was developed. A jet simulator capable of simulating engine intake and exhaust was developed. Simulator calibration. In order to verify the test technology, a simplified fighter test model and model supporting device were developed. The force test was carried out in the Φ3.2m low speed wind tunnel of China Aerodynamic Research and Development Center. The range of attack angle was -5 ° ~ 48 ° , Side slip angle range 0 ° ~ 15 °, the test wind speed of 70m / s. The experimental results show that the test can simulate the fighter engine intake and jet flow more accurately. The intake air flow can be simulated to over 90%, and the maximum jet pressure drop ratio can reach 2.95. This experimental technique provides a new technical approach for studying the effect of intake / jet on the aerodynamic characteristics of fighter jets.