Numerical solutions and laser-Doppler measurements of spin-up

1978 ◽  
Vol 85 (4) ◽  
pp. 609-639 ◽  
Author(s):  
Alex Warn-Varnas ◽  
William W. Fowlis ◽  
Steve Piacsek ◽  
Sang Myung Lee

The spin-up flow in a cylinder of homogeneous fluid has been examined both experimentally and numerically. The primary motivation for this work was to check numerical solution schemes by comparing the numerical results with laboratory measurements obtained with a rotating laser-Doppler velocimeter. The laser-Doppler technique is capable of high accuracy with small space and time resolution, and disturbances of the flow are virtually negligible. A series of measurements was made of the zonal flow over a range of Ekman numbers (1·06 × 10−3≤E≤ 3·30 × 10−3) and Rossby numbers (0·10 [les ]|ε| [les ] 0·33) at various locations in the interior of the flow. These measurements exceed previous ones in accuracy. The weak inertial modes excited by the impulsive start are detectable. The numerical simulations used the primitive equations in axisymmetric form and employed finite-difference techniques on both constant and variable grids. The number of grid points necessary to resolve the Ekman layers was determined. A thorough comparison of the simulations and the experimental measurements is made which includes the details of the amplitude and frequency of the inertial modes. Agreement to within the experimental tolerance is achieved. Analytical results for conditions identical to those in the experiments are not available but some similar linear and nonlinear theories are also compared with the experiments.

1971 ◽  
Vol 10 (4) ◽  
pp. 884 ◽  
Author(s):  
O. Lanz ◽  
C. C. Johnson ◽  
S. Morikawa

Author(s):  
Ken Yoshinaga ◽  
Fumiya Nakashima ◽  
Hirofumi Nogami ◽  
Renshi Sawada

1987 ◽  
Vol 5 (3) ◽  
pp. 193-196 ◽  
Author(s):  
Zihua Zhang ◽  
Jin Wu

1982 ◽  
Vol 21 (10) ◽  
pp. 1785 ◽  
Author(s):  
H. Nishihara ◽  
J. Koyama ◽  
N. Hoki ◽  
F. Kajiya ◽  
M. Hironaga ◽  
...  

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.


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