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題目：Investigation of the Aerospike Nozzle Flow for Space Launcher Propulsion
時(shí)間：2025年6月13日 9:30-11:00
地點(diǎn)：機(jī)械與動(dòng)力工程學(xué)院 振華會(huì)議室
邀請(qǐng)人：彭迪 教授（葉輪機(jī)械研究所）
報(bào)告人簡(jiǎn)介
Christian J. K?hler 博士是德國(guó)慕尼黑聯(lián)邦國(guó)防軍大學(xué)（Universit?t der Bundeswehr München）教授，現(xiàn)任該校流體力學(xué)與空氣動(dòng)力學(xué)研究所所長(zhǎng)。他目前擔(dān)任國(guó)際實(shí)驗(yàn)流體力學(xué)領(lǐng)域期刊《Experiments in Fluids》主編，并入選德國(guó)洪堡基金會(huì)評(píng)選委員會(huì)。他曾擔(dān)任2018年國(guó)際實(shí)驗(yàn)流體力學(xué)大會(huì)及2019年國(guó)際粒子圖像測(cè)速研討會(huì)等國(guó)際會(huì)議主席。K?hler 教授的研究興趣廣泛，涵蓋光學(xué)流場(chǎng)診斷技術(shù)的發(fā)展與應(yīng)用，以及亞音速、跨音速、超音速條件下微流體與湍流中的復(fù)雜流動(dòng)機(jī)理。其合著的第三版《粒子圖像測(cè)速技術(shù)》（Particle Image Velocimetry，PIV）專著已被引用超過8000次。
報(bào)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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