Experimental investigation of the velocity distribution of the attached plane jet after impingement with the corner in a high room

2010 ◽  
Vol 42 (6) ◽  
pp. 935-944 ◽  
Author(s):  
Guangyu Cao ◽  
Mika Ruponen ◽  
Jarek Kurnitski
Keyword(s):  
Experimental Investigation ◽  
Velocity Distribution ◽  
Plane Jet

The Prediction of Velocity Distribution of Plate Jet with a EMMS Model

2015 ◽  
Vol 799-800 ◽  
pp. 629-634
Author(s):  
Ke Zhi Yu ◽  
Hai Zhang ◽  
Yan Ling Liu
Keyword(s):  
Velocity Distribution ◽  
Viscous Dissipation ◽  
Energy Minimization ◽  
Scale Model ◽  
Stability Conditions ◽  
Multi Scale ◽  
Plane Jets ◽  
The Stability ◽  
Plane Jet

The energy minimization multi-scale model is applied to the plane jet. The stability conditions of plane jets is adopted to predict the velocity distribution of plane jet. When the ratio of total dissipation to viscous dissipation tends to the maximum is used as the optimization condition and entrancement factor is considered as a constant, the Gauss velocity distribution can be concluded in the plane jet.

A Theoretical Investigation of the Maximum-Lift Coefficient

1935 ◽  
Vol 2 (1) ◽  
pp. A21-A27
Author(s):  
Th. von Kármán ◽  
Clark B. Millikan
Keyword(s):  
Boundary Layer ◽  
Experimental Investigation ◽  
Reynolds Number ◽  
Velocity Distribution ◽  
Theoretical Investigation ◽  
Laminar Boundary Layer ◽  
Lift Coefficient ◽  
Boundary Layer Theory ◽  
First Approximation ◽  
Transition Points

Abstract In the present paper the application of a laminar boundary-layer theory, previously developed by the authors, to the problem of the maximum-lift coefficient of airfoils is discussed. The calculations are carried through in detail for a first approximation, called a single-roof profile, to the potential velocity distribution over the upper surface of an airfoil. The results indicate a large variation in Clmax with turbulence but the quantitative dependence on Reynolds’ number and turbulence is not satisfactory. The calculations are then repeated for a so-called double-roof profile which approximates to the flow over the upper surface of an N.A.C.A. 2412 airfoil. These results are compared with those obtained from an experimental investigation on the same airfoil. The agreement is considered to indicate that for moderate values of R and Clmax the phenomenon of the maximum-lift coefficient is controlled by a contest between the separation and transition points of the laminar boundary layer over the nose of the airfoil. The difficulties involved in extending the theory to larger values of R, or to airfoils whose Cl vs. α curves are not approximately linear up to the stall, are mentioned.

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