scholarly journals GAP FLOW BEHIND TWO PLATES HAVING ASYMMETRIC BEVELED TRAILING EDGE

2009 ◽  
Vol 37 (4) ◽  
pp. 899-908
Author(s):  
M. M. Mosallem ◽  
Zeinab A. Ahmed ◽  
Abdullah Y. Al-Hossain
2021 ◽  
Author(s):  
Jinkai Xu ◽  
Jin Tao ◽  
Wanfei Ren ◽  
Kun Tian ◽  
Xiaoqing Sun ◽  
...  

Abstract Aiming to solve the problems of the low electrolyte flow rate at leading edge and trailing edge and poor uniformity of the end clearance flow field during the electrochemical machining (ECM) of diffuser blades, a gap flow field simulation model was established by designing three liquid-increasing channels at the leading edge and the trailing edge of the cathode. The simulation results indicate that the liquid-increasing hole channel (LIHC) with an outlet area S of 1.5 mm2 and a distance L from channel center to edge point of 3.2 mm achieves optimal performance. In addition, the experiment results show that the optimized cathode with liquid-increasing hole channel (LIHC) significantly improves the machining efficiency, accuracy and surface quality. Specifically, the feed speed increased from 0.25 mm/min to 0.43 mm/min, the taper decreased from 4.02° to 2.45°, the surface roughness value of blade back reduced from 1.146 µm to 0.802 µm. Moreoever, the roughness of blade basin decreased from 0.961 µm to 0.708 µm, and the roughness of hub reduced from 0.179 µm to 0.119 µm. The results prove the effectiveness of the proposed method, and can be used for ECM of other complex structures with poor flow field uniformity.


2021 ◽  
Author(s):  
Alexander Gordon Jackson

The objectives of this research are to examine the effects of trailing edge modifications of the inboard elevon of a blended-wing-body (BWB) aircraft, the goal being to try and reduce the hinge moment of the inboard elevon through selective aerodynamic design. A computational model was built for 60⁰ and 70⁰ beveled trailing edge modifications, as well as no modification. The inboard elevon was deflected positive 5⁰ and negative 5⁰. The numerical solutions were obtained using an implicit solver and inviscid model. The results of this research showed that, through the use of a beveled trailing edge on the inboard elevon, a maximum of 112% reduction in the hinge moment could be achieved for the negative deflection case and a maximum of 88% reduction in the hinge moment for the positive deflection case. The results showed that there was a significant improvement in the hinge moments, with less that a 2% average change in the overall aerodynamic performance of the BWB for the inviscid models.


2016 ◽  
Vol 384 ◽  
pp. 113-129 ◽  
Author(s):  
W.C.P. van der Velden ◽  
S. Pröbsting ◽  
A.H. van Zuijlen ◽  
A.T. de Jong ◽  
Y. Guan ◽  
...  

Author(s):  
Stefan Pröbsting ◽  
Abhineet Gupta ◽  
Fulvio Scarano ◽  
Yaoyi Guan ◽  
Scott C. Morris

1997 ◽  
Author(s):  
Charles Knight ◽  
Leonard Peltier ◽  
Charles Knight ◽  
Leonard Peltier

Author(s):  
Wouter C. van der Velden ◽  
Stefan Pröbsting ◽  
Arjen de Jong ◽  
Alexander van Zuijlen ◽  
Yaoyi Guan ◽  
...  

AIAA Journal ◽  
2017 ◽  
Vol 55 (5) ◽  
pp. 1757-1762 ◽  
Author(s):  
W. C. P. van der Velden ◽  
A. H. van Zuijlen ◽  
A. T. de Jong ◽  
H. Bijl

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