Numerical modeling of weakly fused fiber-optic polarization beamsplitters. Part II: the three-dimensional electromagnetic model

1998 ◽  
Vol 16 (4) ◽  
pp. 691-696 ◽  
Author(s):  
Szu-Wen Yang ◽  
Tzong-Lin Wu ◽  
Cheng Wen Wu ◽  
Hung-Chun Chang
Author(s):  
Lianjie Li ◽  
Jianxin Li ◽  
Haibo Xie ◽  
Hongqiang Liu ◽  
Li Sun ◽  
...  

Author(s):  
F. Maggio ◽  
M. Liberti ◽  
A. Paffi ◽  
F. Apollonio ◽  
G. d'Inzeo ◽  
...  

2015 ◽  
Vol 33 (11) ◽  
pp. 1350-1359 ◽  
Author(s):  
Jonathan H. Perez ◽  
Fumina Tanaka ◽  
Fumihiko Tanaka ◽  
Daisuke Hamanaka ◽  
Toshitaka Uchino

2001 ◽  
Author(s):  
Abhay A. Watwe ◽  
Ravi S. Prasher

Abstract Traditional methods of estimating package thermal performance employ numerical modeling using commercially available finite-volume or finite-element tools. Use of these tools requires training and experience in thermal modeling. This methodology restricts the ability of die designers to quickly evaluate the thermal impact of their die architecture due to the added throughput time required to enlist the services of a thermal analyst. This paper describes the development of an easy to use spreadsheet tool, which performs quick-turn numerical evaluations of the impact of non-uniform die heating. The tool employs well-established finite-volume numerical techniques to solve the steady-state, three-dimensional Fourier equation of conduction in the package geometry. Minimal input data is required and the inputs are customized using visual basic pull-down menus to assist die designers who may not be thermal experts. Data showing comparison of the estimates from the spreadsheet tool with that obtained from a conventional analysis using the commercially available finite element code ANSYS™ is also presented.


Author(s):  
Abdollah Khodadoust

Abstract The effect of a simulated glaze ice accretion on the flow field of a three-dimensional wing is studied experimentally. A PC-based data acquisition and reduction system was used with a four-beam two-color fiber-optic laser Doppler velocimeter (LDV) to map the flow field along three spanwise cuts on the model. Results of the LDV measurements on the upper surface of the finite wing model without the simulated glaze ice accretion are presented for α = 0 degrees at Reynolds number of 1.5 million. Measurements on the centerline of the clean model compared favorably with theory.


Sign in / Sign up

Export Citation Format

Share Document