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trailing edge
In this paper an investigation is undertaken to explore the nature of the flow in the vicinity of the trailing edge of Joukowski-type airfoil configurations.
      
The analysis carried out over the interaction region of the trailing edge shows that flow separation always takes place beyond certain critical value of the thickness-to-chord ratio parameter under the action of a?self-induced pressure gradient.
      
In this case the flow separation is generated at the trailing edge of a biconvex airfoil, but results are relevant to laminar separation points in general such as that occurring in the leading-edge region.
      
The results indicate that the shock induced bubble plays a leading role in the origin of shock oscillations and the trailing edge has an affect on its amplitude.
      
The effect of spacing distance between the trailing edge of the cavity and the corner was also studied.
      
The results indicate that the Mach stem height depends on the incident shock wave angle and the distance between the trailing edge and the symmetry plane.
      
Existence and regularity of stream functions for subsonic flows past profiles with a sharp trailing edge
      
The aim of this study was to see how far cell responses to moving stimuli fit in with what would be expected from their responses to stationary flashing stimuli.2.Both the leading and the trailing edge of a moving stimulus evoke a transient response.
      
The strength of the trailing edge response increases and reaches the same strength as that of the leading edge response.
      
If the length of a wide moving slit is increased both the leading and the trailing edge responses decrease.
      
OA crossed the obstacles with a reduced step velocity and stepped closer to the trailing edge, although take-off distances were not different between the age groups.
      
The mechanism and signal processing system are described and appraised by comparing stationary and flying wire measurements obtained in the trailing edge region of a flap at an angle of attack which leads to upper-surface separation.
      
This paper presents longitudinal space and space-time conventional velocity correlations measured in the wake of a two-dimensional flat-plate at zero incidence, with fully-turbulent boundary layers at its sharp trailing edge.
      
The chord Reynolds number was one million and the wake measurements extended up to three chord lengths (or nearly 660 trailing edge momentum thicknesses) downstream of the trailing edge.
      
The data indicate rapid interaction of the wall layers immediately behind the trailing edge, leading to significant changes in the flow parameters close to the trailing edge.
      
A visual study is performed in a supersonic, two-dimensional wake; the high value of the Reynolds number ensures that the wake is turbulent from the trailing edge.
      
The flow is seeded by fluid vaporization in one boundary layer upstream of the trailing edge; a light sheet is generated by a Q-switched, high energy ruby laser.
      
The set of photographs taken from the trailing edge up to the far wake is then processed after digitization of the pictures.
      
Simultaneous temperature traces were used to determine the spot's leading and trailing edge characteristics.
      
At very small angles of attack (± 2°), this pressure field extends up to about three chord lengths downstream of the trailing edge of an airfoil device.
      
 

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