Numerical Simulation of Stage Separation with an Unstructured Chimera Grid Method

2004 ◽  
Author(s):  
Sijun Zhang ◽  
Jiwen Liu ◽  
Yensen Chen ◽  
Xiang Zhao
Keyword(s):  
Numerical Simulation ◽  
Grid Method ◽  
Stage Separation ◽  
Chimera Grid

Numerical simulation of an X-wing flapping wing MAV by means of a deforming overset grid method

2015 ◽  
Author(s):  
Shuanghou Deng ◽  
Tianhang Xiao ◽  
Mustafa Percin ◽  
Bas van Oudheusden ◽  
Hester Bijl ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Grid Method ◽  
Flapping Wing ◽  
Overset Grid ◽  
Overset Grid Method

Utilization of Cold-Flow Numerical Simulation With Overset Grid Method in Development Process of Aeroengine Combustor

2010 ◽  
Author(s):  
Mitsumasa Makida ◽  
Naoki Nakamura ◽  
Osamu Nozaki
Keyword(s):  
Numerical Simulation ◽  
Development Process ◽  
Grid Method ◽  
Simulation Method ◽  
Simulation Methods ◽  
Overset Grid ◽  
Simulation Code ◽  
Screening Process ◽  
Cold Flow ◽  
Overset Grid Method

In the TechCLEAN project of JAXA, a combustor for a small aircraft engine has been developed. The combustor was tuned to show the behavior of the Rich-Lean combustion through combustion tests under atmospheric and practical conditions. In the development process of the combustor, numerical simulation methods were also utilized as analysis tools to accelerate the development of the combustor. To use in the screening process of the combustor design, we focused on cost-effective simulation methods and adopted the cold-flow RANS simulation code UPACS which has been developed in JAXA. And to simplify the treatment of calculation grids of the combustor with complicated configuration, we also utilized combination of the overset grid method with the attached multi-block grid method. This simulation method was applied to three phases in the combustor development process; first to the analysis of the combustor configuration to adjust the overall pressure loss, secondly to the analysis of flame stability, and thirdly to the tuning of air flow ratio to optimize emission characteristics of full annular combustors. Finally, the full annular combustor was successively tuned to reduce NOx emissions to 38.1% of the ICAO CAEP4 standard under ICAO LTO cycles, also sustaining basic performances as an aircraft combustor.

Navier–Stokes solver for water entry bodies with moving Chimera grid method in 6DOF motions

2016 ◽  
Vol 140 ◽  
pp. 19-38 ◽  
Author(s):  
Van-Tu Nguyen ◽  
Duc-Thanh Vu ◽  
Warn-Gyu Park ◽  
Chul-Min Jung
Keyword(s):  
Grid Method ◽  
Water Entry ◽  
Navier Stokes ◽  
Chimera Grid

Numerical simulation of stage separation manoeuvre with jet interaction

2006 ◽  
Vol 78 (3) ◽  
pp. 217-225 ◽  
Author(s):  
Masoud Mirzaei ◽  
Babak Najafie Nia ◽  
Abodollah Shadaram
Keyword(s):  
Numerical Simulation ◽  
Jet Interaction ◽  
Stage Separation
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