Thermal Fluid System Design: Rocket Engine Layout – Cycle Calculation Nozzle Design & Cooling Turbopump Secondary Flow Systems Propellant Pipelines Generative Turbomachinery Design & Analysis: Oxidizer & Fuel Pump Design & Analysis Subsonic and Supersonic Turbine Design & Analysis ...
and Onofri, M.: Numerical calculation of FSS/RSS transition in highly overexpanded rocket nozzle flows, Shock Waves J., Vol. 20, No.1, pp. 139-146, 2010.Martelli, E., Nasuti, F., Onofri, M.: Numerical calculation of FSS/RSS transition in highly overexpanded rocket nozzle flows. ...
A method which combines MacCormark scheme with the characteristic line method is used to calculate the two phase flow in solid rocket motor nozzle. In transonic region, the gas-phase governing equations are solved by time-dependent method based on MacCormark explicit scheme, while the partical ...
A procedure for calculation of boundary layer trip protuberances in overexpanded rocket nozzles 来自 ResearchGate 喜欢 0 阅读量: 21 作者: RH Schmucker 摘要: A procedure is described for sizing, scaling, positioning and performance loss calculation of a boundary layer trip protuberance. The ...
rocket-motor-nozzle 例句 释义: 全部 更多例句筛选 1. Contour design and numerical calculation of certain solid propellant rocket motor nozzle 某型号固体火箭发动机喷管型面设计与数值计算 ilib.cn 2. Gap design of solid rocket motor nozzle structures 固体火箭发动机喷管结构缝隙设计 ilib.cn©...
The details of nozzle design depend strongly on application. Most applications require at least some use of insulation or special high-temperature materials (e.g.,graphite) in order to protect the load-carrying structures from thermal failure. Many applications require that the direction of the exha...
lower oxidizer mass fraction. The inlet pressure and temperature of the nozzle were positively correlated with the ablation rate, with the temperature having a more significant impact than the pressure. These findings provide theoretical guidance for the thermal protection design of rocket engine nozzle...
The combustor is assumed to have a concentrated combustion zone and a zero length nozzle. The nonl... MITCHELL,E C. - 《Combustion Science & Technology》 被引量: 6发表: 1970年 Progress and Challenges in Liquid Rocket Combustion Stability Modeling Progress and challenges in combustion stability ...
发明人: ロバート ブロガン 摘要: PURPOSE: To raise the combustion temperature and the temperature of exhaust mushroom cloud easily and reduce thrust strength by providing a nozzle having a substantially cylindrical outer wall and a cup-shaped member arranged therein.收藏...
lateral loads may be induced. The sideload character strongly depends on the nozzle design, and is a key dimensional load for the nozzle’s mechanical structure. It is shown especially for the VULCAIN and VULCAIN 2 nozzle, how specific shock pattern evolve during transients, and how - by the...