题目：Investigation of the Aerospike Nozzle Flow for Space Launcher Propulsion
时间：2025年6月13日 9:30-11:00
地点：yl23411永利 振华会议室
邀请人：彭迪 教授（叶轮机械研究所）
报告人简介
Christian J. Kähler 博士是德国慕尼黑联邦国防军大学（Universität der Bundeswehr München）教授，现任该校流体力学与空气动力学研究所所长。他目前担任国际实验流体力学领域权威期刊《Experiments in Fluids》主编，并入选德国洪堡基金会评选委员会。他曾担任2018年国际实验流体力学大会及2019年国际粒子图像测速研讨会等国际会议主席。Kähler 教授的研究兴趣广泛，涵盖光学流场诊断技术的发展与应用，以及亚音速、跨音速、超音速条件下微流体与湍流中的复杂流动机理。其合著的第三版《粒子图像测速技术》（Particle Image Velocimetry，PIV）专著已被引用超过8000次。
报告摘要
The plug/aerospike nozzle is a promising concept for use as a propulsion system for space launchers and space planes. The ability to adapt the nozzle jet to the ambient pressure level enhances thrust performance under overexpanded operating conditions compared to conventional bell nozzles. This feature is of great interest for future single-stage-to-orbit (SSTO) vehicles. This experimental research project investigates the topology and aerodynamics of a cold flow linear plug nozzle jet in an outer flow environment at the Trisonic Wind tunnel Munich (TWM). High-speed PIV and schlieren measurements are used to understand the mutual aerodynamic interaction between each other. The jet flow is studied for a variety of nozzle pressure ratios in combination with an outer flow at sub-, trans-, and supersonic Mach numbers. An examination of the flow is conducted for two plug lengths. It is noted that a truncated plug lowers the weight and reduces the risk of overheating in contrast to a long spike. In present studies, a newer wind tunnel model version is designed to study aerodynamic effects of a modular/clustered linear aerospike nozzle, while enabling thrust vector control strategies.
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地址：上海市东川路800号永利官网闵行校区yl23411永利
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