{"title":"Development of a Small Modular Multi-Stage Axial Compressor for Ice Crystal Icing Research","authors":"T. Currie","doi":"10.2514/6.2018-4133","DOIUrl":"https://doi.org/10.2514/6.2018-4133","url":null,"abstract":"","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"54 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122999610","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Numerical study on the condensed and frozen water vapor on a flat plate using an open source code","authors":"Soomin Park, H. Kihara, K. Abe","doi":"10.2514/6.2018-3018","DOIUrl":"https://doi.org/10.2514/6.2018-3018","url":null,"abstract":"","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131566285","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
V. Tenishev, D. Borovikov, M. Combi, I. Sokolov, T. Gombosi
{"title":"Toward development of the energetic particle radiation nowcast model for assessing the radiation environment in the altitude range from that used by the commercial aviation in the troposphere to LEO, MEO, and GEO","authors":"V. Tenishev, D. Borovikov, M. Combi, I. Sokolov, T. Gombosi","doi":"10.2514/6.2018-3650","DOIUrl":"https://doi.org/10.2514/6.2018-3650","url":null,"abstract":"","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127664215","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
E. Montreuil, W. Ghedhaifi, Vivien Chmielarski, V. François, F. Gand, A. Loseille
Aircraft contrails may contribute to the global radiative forcing. In this context, the investigation of contrail formation in the near field of an aircraft may be helpful in developing strategies to reduce undesirable impacts. Contrail formation is also a complex topic, since several physical processes are involved, covering a large range of space and time scales, from the engine exit to the atmospheric global scale. In the near field of the aircraft, contrail formation is mainly dominated by microphysics and mixing processes between the propelling jets and the external flow (the so called jet-vortex interaction). In this study, three-dimensional Reynolds-Averaged Navier–Stokes (RANS) simulations of contrails produced by the Common Research Model wing/body/engine configuration during cruise flights is performed. In the present work, a dedicated internal nozzle geometry has been designed to replace the through flow nacelle of the original CRM configuration. Thus, the engine core and bypass flows are actually computed in the simulations, which allows several parametrical studies and avoids using parameterizations to describe the plume's dilution. The objective is to simulate the early development of contrails in a fresh plume whose dilution is obtained with a spatial simulation of jet/vortex interaction. A coupling is carried out with a chemical and a microphysical model implemented in the unstructured Navier-Stokes CFD code CEDRE to simulate particle growth using an Eulerian approach. The implemented microphysics model can simulate water condensation onto soot particles, taking into account their activation by adsorption of sulfur species. In this context, an adaptation grid mesh procedure has been used in order to generate an optimized unstructured mesh in the fluid zone of interest (i.e. vortex wake and jet exhaust).
飞机尾迹可能对全球辐射强迫有贡献。在这种情况下，对飞机近场尾迹形成的研究可能有助于制定减少不良影响的策略。尾迹的形成也是一个复杂的话题，因为它涉及多个物理过程，涵盖了大范围的空间和时间尺度，从发动机出口到大气全球尺度。在飞机近场，尾迹的形成主要是由微物理和推进射流与外部气流的混合过程(即所谓的射流-涡相互作用)主导的。在这项研究中，对巡航飞行中由通用研究模型机翼/机身/发动机配置产生的尾迹进行了三维reynolds - average Navier-Stokes (RANS)模拟。在目前的工作中，设计了一个专用的内部喷嘴几何形状，以取代原始CRM配置的直通流机舱。因此，在模拟中实际上计算了发动机核心和旁道流动，这允许进行几个参数化研究，并避免使用参数化来描述羽流的稀释。目的是模拟新的羽流中尾迹的早期发展，其稀释是通过射流/涡相互作用的空间模拟得到的。在非结构化Navier-Stokes CFD代码CEDRE中实现了化学模型和微物理模型的耦合，使用欧拉方法模拟颗粒生长。所实现的微物理模型可以模拟水在烟灰颗粒上的凝结，并考虑烟灰颗粒吸附硫的活化作用。在这种情况下，为了在感兴趣的流体区域(即旋涡尾迹和射流排气)中生成优化的非结构化网格，使用了自适应网格程序。
{"title":"Numerical Simulation of contrail formation on the Common Research Model wing/body/engine configuration","authors":"E. Montreuil, W. Ghedhaifi, Vivien Chmielarski, V. François, F. Gand, A. Loseille","doi":"10.2514/6.2018-3189","DOIUrl":"https://doi.org/10.2514/6.2018-3189","url":null,"abstract":"Aircraft contrails may contribute to the global radiative forcing. In this context, the investigation of contrail formation in the near field of an aircraft may be helpful in developing strategies to reduce undesirable impacts. Contrail formation is also a complex topic, since several physical processes are involved, covering a large range of space and time scales, from the engine exit to the atmospheric global scale. In the near field of the aircraft, contrail formation is mainly dominated by microphysics and mixing processes between the propelling jets and the external flow (the so called jet-vortex interaction). In this study, three-dimensional Reynolds-Averaged Navier–Stokes (RANS) simulations of contrails produced by the Common Research Model wing/body/engine configuration during cruise flights is performed. In the present work, a dedicated internal nozzle geometry has been designed to replace the through flow nacelle of the original CRM configuration. Thus, the engine core and bypass flows are actually computed in the simulations, which allows several parametrical studies and avoids using parameterizations to describe the plume's dilution. The objective is to simulate the early development of contrails in a fresh plume whose dilution is obtained with a spatial simulation of jet/vortex interaction. A coupling is carried out with a chemical and a microphysical model implemented in the unstructured Navier-Stokes CFD code CEDRE to simulate particle growth using an Eulerian approach. The implemented microphysics model can simulate water condensation onto soot particles, taking into account their activation by adsorption of sulfur species. In this context, an adaptation grid mesh procedure has been used in order to generate an optimized unstructured mesh in the fluid zone of interest (i.e. vortex wake and jet exhaust).","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125354736","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Fracture of Ice at Interfaces from Molecular Dynamics Simulations","authors":"A. Afshar, Jing Zong, D. Thompson, D. Meng","doi":"10.2514/6.2018-3017","DOIUrl":"https://doi.org/10.2514/6.2018-3017","url":null,"abstract":"","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"86 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123593378","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
One of the main limitations of the operational envelope of UAVs today is the risk of atmospheric icing. UAV icing is not well researched and this paper aims to generate a better understanding of how ice accretion and aerodynamic performance degradation on UAV airfoils can be simulated. In particular, the objective is to investigate how well a panel-method based code compares to a modern CFD icing code. LEWICE and FENSAP-ICE are used to generate three characteristic 2D ice shapes (rime, glaze, mixed) on a NREL S826 airfoil for low Reynolds numbers. RANS calculations are performed to assess the resulting aerodynamic performance degradation. Validation of the ice growth predictions is achieved by using literature data. Aerodynamic performance degradation is validated with experimental results from a (non-icing) wind tunnel at NTNU. The numerical results indicate that icing morphology has a major influence on the ability of both codes to capture ice shape and aerodynamic penalties. Rime is simulated consistently, whereas predictions for mixed and glaze show significant differences. All ice cases negatively impact the aerodynamic performance by reducing maximum lift, decreasing stall angle and increasing drag.
{"title":"UAV Icing: Comparison of LEWICE and FENSAP-ICE for Ice Accretion and Performance Degradation","authors":"R. Hann","doi":"10.2514/6.2018-2861","DOIUrl":"https://doi.org/10.2514/6.2018-2861","url":null,"abstract":"One of the main limitations of the operational envelope of UAVs today is the risk of atmospheric icing. UAV icing is not well researched and this paper aims to generate a better understanding of how ice accretion and aerodynamic performance degradation on UAV airfoils can be simulated. In particular, the objective is to investigate how well a panel-method based code compares to a modern CFD icing code. LEWICE and FENSAP-ICE are used to generate three characteristic 2D ice shapes (rime, glaze, mixed) on a NREL S826 airfoil for low Reynolds numbers. RANS calculations are performed to assess the resulting aerodynamic performance degradation. Validation of the ice growth predictions is achieved by using literature data. Aerodynamic performance degradation is validated with experimental results from a (non-icing) wind tunnel at NTNU. The numerical results indicate that icing morphology has a major influence on the ability of both codes to capture ice shape and aerodynamic penalties. Rime is simulated consistently, whereas predictions for mixed and glaze show significant differences. All ice cases negatively impact the aerodynamic performance by reducing maximum lift, decreasing stall angle and increasing drag.","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123641640","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
J. V. Zante, T. Ratvasky, T. Bencic, Clark C. Challis, Emily N. Timko, Mark R. Woike
NASA Glenn’s Propulsion Systems Lab, an altitude engine test facility, generates icing clouds with a spray system. While the spray system is used mostly to create ice crystal clouds (Appendix D/P), the 2017 cloud characterization effort added the requirement to produce exactly supercooled liquid clouds in Appendix C and Appendix O. Success was demonstrated to supercool the largest drops at the warmest conditions
{"title":"Update on the NASA Glenn Propulsion Systems Lab Icing and Ice Crystal Cloud Characterization - 2017","authors":"J. V. Zante, T. Ratvasky, T. Bencic, Clark C. Challis, Emily N. Timko, Mark R. Woike","doi":"10.2514/6.2018-3969","DOIUrl":"https://doi.org/10.2514/6.2018-3969","url":null,"abstract":"NASA Glenn’s Propulsion Systems Lab, an altitude engine test facility, generates icing clouds with a spray system. While the spray system is used mostly to create ice crystal clouds (Appendix D/P), the 2017 cloud characterization effort added the requirement to produce exactly supercooled liquid clouds in Appendix C and Appendix O. Success was demonstrated to supercool the largest drops at the warmest conditions","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121634689","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
E. Radenac, A. Kontogiannis, Charlotte Bayeux, P. Villedieu
{"title":"An extended rough-wall model for an integral boundary layer model intended for ice accretion calculations","authors":"E. Radenac, A. Kontogiannis, Charlotte Bayeux, P. Villedieu","doi":"10.2514/6.2018-2858","DOIUrl":"https://doi.org/10.2514/6.2018-2858","url":null,"abstract":"","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133169573","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
M. King, W. Bachalo, D. Bell, Laura-Cheri King-Steen
A study of the Weber Number effects on droplets in the NASA Icing Research Tunnel is described. The work focuses on examining the droplet Weber Number effects observed for droplets accelerated by air flow in the contraction section of the Icing Research Tunnel to the test section. These results will aid in Supercooled Large Drop facility design studies. Measurements acquired with the Phase Doppler Interferometer and High Speed Imaging Dual Range Flight Probes at a series of locations through the contraction are presented alongside a 1D numerical model developed during this study to aid interpretation of the experimental results. An estimate of the maximum Weber Number observed in the Icing Research Tunnel for varying drop sizes up to 1000 μm is presented and provided for incorporation into future design studies. Finally, experimental results coupled with a numerical model indicate that breakup of drops up to 1000 μm is not occurring in the NASA Icing Research Tunnel up to 129 m/s.
{"title":"Weber Number Tests in the NASA Icing Research Tunnel","authors":"M. King, W. Bachalo, D. Bell, Laura-Cheri King-Steen","doi":"10.2514/6.2018-3184","DOIUrl":"https://doi.org/10.2514/6.2018-3184","url":null,"abstract":"A study of the Weber Number effects on droplets in the NASA Icing Research Tunnel is described. The work focuses on examining the droplet Weber Number effects observed for droplets accelerated by air flow in the contraction section of the Icing Research Tunnel to the test section. These results will aid in Supercooled Large Drop facility design studies. Measurements acquired with the Phase Doppler Interferometer and High Speed Imaging Dual Range Flight Probes at a series of locations through the contraction are presented alongside a 1D numerical model developed during this study to aid interpretation of the experimental results. An estimate of the maximum Weber Number observed in the Icing Research Tunnel for varying drop sizes up to 1000 μm is presented and provided for incorporation into future design studies. Finally, experimental results coupled with a numerical model indicate that breakup of drops up to 1000 μm is not occurring in the NASA Icing Research Tunnel up to 129 m/s.","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"203 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116356882","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Ice accretion on a NACA 23012 airfoil","authors":"E. Oztekin, J. Riley","doi":"10.2514/6.2017-3760","DOIUrl":"https://doi.org/10.2514/6.2017-3760","url":null,"abstract":"","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130953931","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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