Discussion: “Supersonic Compressor Cascades—An Analysis of the Entrance Region Flow Field Containing Detached Shock Waves” (York, R. E., and Woodard, H. S., 1976, ASME J. Eng. Power, 98, pp. 247–254)

1976 ◽  
Vol 98 (2) ◽  
pp. 255-256
Author(s):  
D. C. Prince
Keyword(s):  
Shock Waves ◽  
Flow Field ◽  
Entrance Region ◽  
Region Flow

Entrance region flow of polymer melts

AIChE Journal ◽  
1971 ◽  
Vol 17 (6) ◽  
pp. 1480-1485 ◽  
Author(s):  
Chang Dae Han
Keyword(s):  
Polymer Melts ◽  
Entrance Region ◽  
Region Flow

Approximate inviscid, nonadiabatic stagnation region flow field solution

AIAA Journal ◽  
1965 ◽  
Vol 3 (8) ◽  
pp. 1537-1538 ◽  
Author(s):  
G. M. HANLEY ◽  
K. D. KORKAN
Keyword(s):  
Flow Field ◽  
Stagnation Region ◽  
Field Solution ◽  
Region Flow

Experimental Analysis of Microchannel Entrance Length Characteristics Using Microparticle Image Velocimetry

2010 ◽  
Vol 132 (4) ◽  
Author(s):  
Tariq Ahmad ◽  
Ibrahim Hassan
Keyword(s):  
Reynolds Number ◽  
Flow Field ◽  
Entrance Region ◽  
Working Fluid ◽  
Parallel Plates ◽  
Entrance Length ◽  
Number Range ◽  
Micro Piv ◽  
Image Velocimetry ◽  
Microparticle Image Velocimetry

The study of the entrance region of microchannels and microdevices is limited, yet important, since the effect on the flow field and heat transfer mechanisms is significant. An experimental study has been carried out to explore the laminar hydrodynamic development length in the entrance region of adiabatic square microchannels. Flow field measurements are acquired through the use of microparticle image velocimetry (micro-PIV), a nonintrusive particle tracking and flow observation technique. With the application of micro-PIV, entrance length flow field data are obtained for three different microchannel hydraulic diameters of 500 μm, 200 μm, and 100 μm, all of which have cross-sectional aspect ratios of 1. The working fluid is distilled water, and velocity profile data are acquired over a laminar Reynolds number range from 0.5 to 200. The test-sections were designed as to provide a sharp-edged microchannel inlet from a very large reservoir at least 100 times wider and higher than the microchannel hydraulic diameter. Also, all microchannels have a length-to-diameter ratio of at least 100 to assure fully developed flow at the channel exit. The micro-PIV procedure is validated in the fully developed region with comparison to Navier–Stokes momentum equations. Good agreement was found with comparison to conventional entrance length correlations for ducts or parallel plates, depending on the Reynolds range, and minimal influence of dimensional scaling between the investigated microchannels was observed. New entrance length correlations are proposed, which account for both creeping and high laminar Reynolds number flows. These correlations are unique in predicting the entrance length in microchannels and will aid in the design of future microfluidic devices.

Supersonic and hypersonic flow with attached shock waves over delta wings

1971 ◽  
Vol 325 (1561) ◽  
pp. 251-268 ◽  
Keyword(s):  
Shock Waves ◽  
Flow Field ◽  
Hypersonic Flow ◽  
Delta Wing ◽  
Cross Flow ◽  
Flow Region ◽  
Lower Surface ◽  
Uniform Flow ◽  
Nonuniform Flow ◽  
Sonic Line

A unified theory is developed for supersonic and hypersonic flow with attached shock waves over the lower surface of a delta wing at an angle of attack. The flow field on the lower surface of a delta wing consists of uniform flow regions near the leading edges, where the cross flow is supersonic and a nonuniform flow region near the central part, where the cross flow is subsonic. In the nonuniform flow region, the theory is based on the assumption that the flow differs slightly from the corresponding two-dimensional flow over a flat plate. Thus a linearized perturbation on a nonlinear flow field is first calculated and then strained and corrected so that the flow is matched continuously to the uniform flow which is obtained exactly. When compared with available exact numerical solutions the theory gives, in all cases, almost identical results, except near the crossflow sonic line where existing numerical methods fail to produce a discontinuous slope in the pressure curve, whereas the present theory predicts such a discontinuity and shows that the slope has a square root singularity at the crossflow sonic line similar to that in the supersonic linear theory.

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