scholarly journals Numerical Simulation of Monodisperse Lube Oil Multiple Droplet Evaporation and Autoignition under Nonconstant Cylinder Conditions of Low-Speed Two-Stroke Gas Engines

ACS Omega ◽  
2021 ◽  
Author(s):  
Zixin Wang ◽  
Ping Yi ◽  
Wenjing Qu ◽  
Liyan Feng ◽  
Zhen Gong
Keyword(s):  
Numerical Simulation ◽  
Droplet Evaporation ◽  
Low Speed

Numerical Simulation of Ethanol−Water−NaCl Droplet Evaporation

2010 ◽  
Vol 49 (12) ◽  
pp. 5631-5643 ◽  
Author(s):  
Xingmao Jiang ◽  
Timothy L. Ward ◽  
Frank van Swol ◽  
C. Jeffrey Brinker
Keyword(s):  
Numerical Simulation ◽  
Droplet Evaporation

scholarly journals Numerical Simulation for Engine/Airframe Interaction Effects of the BWB300 on Aerodynamic Performances

2019 ◽  
Vol 2019 ◽  
pp. 1-15 ◽  
Author(s):  
Gang Yu ◽  
Dong Li ◽  
Yue Shu ◽  
Zeyu Zhang
Keyword(s):  
Numerical Simulation ◽  
High Speed ◽  
Separated Flow ◽  
Simulation Method ◽  
Interaction Effects ◽  
Surface Flow ◽  
Concept Design ◽  
Aerodynamic Forces ◽  
Low Speed ◽  
Aerodynamic Performances

The engine/airframe interaction effects of the BWB300 on aerodynamic performances were analyzed by using the numerical simulation method. The BWB300 is a 300-seat Blended Wing Body airplane designed by the Airplane Concept Design Institute of Northwestern Polytechnical University. The engine model used for simulation was simplified as a powered nacelle. The results indicated the following: at high speed, although the engine/airframe interaction effects on the aerodynamic forces were not significant, the airframe’s upper surface flow was greatly changed; at low speed, the airframe’s aerodynamic forces (of the airplane with/without the engine) were greatly different, especially at high attack angles, i.e., the effect of the engine suction caused the engine configuration aerodynamic forces of the airframe to be bigger than those without the engine; and the engine’s installation resulting in the different development of flow separation at the airframe’s upper surface caused greater obvious differences between the 2 configurations at high angles and low speed. Moreover, at low-speed high attack angles, the separated flow from the blended area caused serious distortion at the fan inlet of the engine.

scholarly journals Numerical Simulation of Rotor Clocking Effect in a Low-Speed Compressor

2003 ◽  
Vol 16 (3) ◽  
pp. 129-137
Author(s):  
Hai-tao YANG ◽  
Hong-yan HUANG ◽  
Guo-tai FENG ◽  
Jie-xian SU ◽  
Wei-rong SUN
Keyword(s):  
Numerical Simulation ◽  
Low Speed

Numerical Simulation Method for 3D Low Speed Micro Flapping-Wing with Complex Kinematics

2011 ◽  
Vol 308-310 ◽  
pp. 332-335
Author(s):  
Wen Qing Yang ◽  
Bi Feng Song ◽  
Wen Ping Song ◽  
Zhan Ke Li ◽  
Ya Feng Zhang
Keyword(s):  
Numerical Simulation ◽  
Numerical Method ◽  
Stokes Equations ◽  
Simulation Method ◽  
Flapping Wing ◽  
Design Tool ◽  
Navier Stokes ◽  
Low Speed ◽  
Wing Motion ◽  
Numerical Simulation Method

A numerical simulation method is presented in this paper for 3D low speed micro flapping-wing with complex kinematics. The main characteristics for the numerical simulation of Flapping-wing Micro Air Vehicle (FMAV) include: low speed, big range of wing motion, and complex kinematics. The low speed problem is solved by preconditioning method. The big range of wing motion problem is solved by chimera grid system. The problem of complex kinematics is solved by decomposed into three main motions, i.e. plunging, pitching, and swing respectively. The numerical method is solving the Reynolds Averaged Navier-Stokes equations for the viscous flow over micro flapping-wing. The numerical method of this paper is validated by good accordance with experimental results of reference. This method can used to simulate the aerodynamic performance of micro flapping-wing with complex kinematics in low speed and is helpful to the FMAV designers as a design tool.

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