Micro-propulsion is considered to be the emerging technology for the propulsion of micro and micro aerospace vehicles as it is preferred over mesoscale thruster due to lower overall life-cycle cost and launching costs. Hence this paper investigates the influence of critical parameters like the Nozzle Pressure Ratio (NPR) and Reynolds number (Re) on the operational characteristics of the micronozzle. A conical nozzle with throat diameter 710 µm and exit/throat area ratio ∼2.14 has been designed and is analyzed numerically by using a model based on pressure-based coupled implicit for various NPR, the backpressure with three Res namely, 1000, 1500, and 2000. The performance of this micronozzle has been characterized in terms of thrust, thrust coefficient, and specific impulse for all three Re cases. A subsequent analysis of the subsonic layer reveals that the nozzle is subjected to high viscous losses at low NPRs, which are independent of Re.

中文翻译：

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锥形微喷嘴高温气流的数值分析

微型推进被认为是微型和微型航空航天飞机推进的新兴技术，因为它具有较低的总生命周期成本和发射成本，因此比中型推进器更受青睐。因此，本文研究了关键参数如喷嘴压力比（NPR）和雷诺数（Re）对微喷嘴工作特性的影响。设计了一个直径为710 µm，出口/出口面积比为〜2.14的圆锥形喷嘴，并使用基于压力的耦合隐式模型对各种NPR，具有三个Res的背压分别为1000、1500和1000进行了数值分析。 2000年。针对这三个Re案例，已根据推力，推力系数和比冲对这种微喷嘴的性能进行了表征。