{"title":"Transonic Flow Field Analysis of a Minimum Nozzle Length Rocket Engine","authors":"O. Abada, H. Kbab, S. Haif","doi":"10.13111/2066-8201.2024.16.2.1","DOIUrl":null,"url":null,"abstract":"The aim of this paper is to develop a profile of axisymmetric minimum length nozzle giving a uniform and parallel flow at the exit section. The study is done at high temperature, lower than the dissociation threshold of the molecules. The design is made by the method of characteristics (MOC). The variation of the specific heats with the temperature is considered. The numerical results have been validated with CFD simulation Ansys-Fluent software. The second part of this study is to calculate and analyze the transonic flow field of this supersonic nozzle. The computation of the flow field characteristics at the throat is thus essential to the nozzle developed thrust value and therefore to the aircraft or rocket it propels. An investigation was conducted to analyze the effects of parameters on the position of the sonic line. These parameters include stagnation temperature T0, radius of the nozzle, types of gases, and exit Mach number ME.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":" 1031","pages":""},"PeriodicalIF":0.0000,"publicationDate":"2024-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"INCAS Bulletin","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.13111/2066-8201.2024.16.2.1","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q2","JCRName":"Engineering","Score":null,"Total":0}
引用次数: 0
Abstract
The aim of this paper is to develop a profile of axisymmetric minimum length nozzle giving a uniform and parallel flow at the exit section. The study is done at high temperature, lower than the dissociation threshold of the molecules. The design is made by the method of characteristics (MOC). The variation of the specific heats with the temperature is considered. The numerical results have been validated with CFD simulation Ansys-Fluent software. The second part of this study is to calculate and analyze the transonic flow field of this supersonic nozzle. The computation of the flow field characteristics at the throat is thus essential to the nozzle developed thrust value and therefore to the aircraft or rocket it propels. An investigation was conducted to analyze the effects of parameters on the position of the sonic line. These parameters include stagnation temperature T0, radius of the nozzle, types of gases, and exit Mach number ME.
期刊介绍：
INCAS BULLETIN is a scientific quartely journal published by INCAS – National Institute for Aerospace Research “Elie Carafoli” (under the aegis of The Romanian Academy) Its current focus is the aerospace field, covering fluid mechanics, aerodynamics, flight theory, aeroelasticity, structures, applied control, mechatronics, experimental aerodynamics, computational methods. All submitted papers are peer-reviewed. The journal will publish reports and short research original papers of substance. Unique features distinguishing this journal: R & D reports in aerospace sciences in Romania The INCAS BULLETIN of the National Institute for Aerospace Research "Elie Carafoli" includes the following sections: 1) FULL PAPERS. -Strength of materials, elasticity, plasticity, aeroelasticity, static and dynamic analysis of structures, vibrations and impact. -Systems, mechatronics and control in aerospace. -Materials and tribology. -Kinematics and dynamics of mechanisms, friction, lubrication. -Measurement technique. -Aeroacoustics, ventilation, wind motors. -Management in Aerospace Activities. 2) TECHNICAL-SCIENTIFIC NOTES and REPORTS. Includes: case studies, technical-scientific notes and reports on published areas. 3) INCAS NEWS. Promote and emphasise INCAS technical base and achievements. 4) BOOK REVIEWS.
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