NUMERICAL SIMULATION FOR A FLOW AROUND BODY EJECTION USING AN AXISYMMETRIC UNSTRUCTURED MOVING GRID METHOD

2012 ◽  
Vol 4 (3) ◽  
pp. 217-223 ◽  
Author(s):  
Masashi Yamakawa ◽  
Daiki Takekawa ◽  
Kenichi Matsuno ◽  
Shinichi Asao
Keyword(s):  
Numerical Simulation ◽  
Grid Method ◽  
Moving 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

Solving moving boundary problems with an adaptive moving grid method

1998 ◽  
Vol 53 (19) ◽  
pp. 3393-3411 ◽  
Author(s):  
Jörg Frauhammer ◽  
Harald Klein ◽  
Gerhart Eigenberger ◽  
Ulrich Nowak
Keyword(s):  
Moving Boundary ◽  
Grid Method ◽  
Moving Boundary Problems ◽  
Moving Grid ◽  
Boundary Problems

scholarly journals Numerical Simulation of Rotor in Hover and Forward Flight

2018 ◽  
Vol 179 ◽  
pp. 03011
Author(s):  
Qinghe Zhao
Keyword(s):  
Experimental Data ◽  
Numerical Simulation ◽  
Flow Field ◽  
Moving Grid ◽  
Steady State Flow ◽  
Forward Flight ◽  
Numerical Simulation Result ◽  
Structured Grid ◽  
Pressure Distributions ◽  
Good Agreement

The flow around rotor is numerical simulated in hover and forward flight based on multi-structured grid. In hover the flow field can be transformed into a steady-state flow field in the rotating coordinate system. The experimental data of Caradonna and Tung rotor is used to verify the numerical simulation result. The numerical results compare well with the experimental data for both non-lifting and lifting cases. Non-lifting forward flight is simulated and the prediction capabilities have been validated through the ONERA two-blade rotor. The pressure distributions of different positions under different azimuth angles are compared, which is in good agreement with the experimental data. There is unsteady shock wave when forward flight. Dual-time method is used to obtain unsteady flow field with rigid moving grid in the inertial system.

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.

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