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In the inverse problem for supersonic and subsonic flows, expressions are derived for finding the wing geometry from given values of the load on the wing and the variation of the load along the span of the wing.
      
Laminar boundary layer on swept-back wings of infinite span at an angle of attack
      
A study is made of the flow of a compressible gas in a laminar boundary layer on swept-back wings of infinite span in a supersonic gas flow at different angles of attack.
      
Influence of transverse slits on the hydrodynamic coefficients of a wing of finite span in stationary and nonstationary motion n
      
The problem of irrotational flow past a wing of finite thickness and finite span can be reduced by Green's formula to the solution of a system of Fredholm equations of the second kind on the surface of the wing [1].
      
At the same time, a discretization is also realized for the wake vortex sheet along the span of the wing.
      
In the present paper, this idea of numerical solution of the problem of irrotational flow past a wing of finite span is realized on the basis of an approximation of the unknown functions which is piecewise linear along the span.
      
The present paper continues earlier work of the authors [1, 2] on boundary layers in the neighborhood of a symmetry plane and on sweptback wings of infinite span.
      
Investigation of the shape of the free surface of the liquid in the case of planing of a plate of finite span
      
Numerical investigation of the hypersonic viscous shock layer on wings of infinite span at angles of attack and slip
      
In the framework of the theory of a hypersonic viscous shock layer [1] with modified Rankine-Hugoniot relations [2] at the shock wave a study is made of flow past wings of infinite span with a rounded leading edge.
      
Investigation of hypersonic flow of rarefied gas past wings of infinite span
      
In [1] the maximum efficiency was found for a vibrating wing of infinite span in a supersonic flow.
      
Within the framework of the theory of a hypersonic viscous shock layer a study is made of flow round wings of infinite span with blunt leading edges at various angles of attack and slip.
      
Bounded flow sound a supercavitating wing of finite span
      
Ideal incompressible flow over a thin wing of finite span with large-amplitude oscillations
      
Investigation of the flow past wings of infinite span with a blunt leading edge in the vorticity interaction regime
      
An asymptotic analysis of the Navier-Stokes equations is carried out for the case of hypersonic flow past wings of infinite span with a blunt leading edge when ? → 0, Re → ∞, and M∞ → ∞.
      
Unsteady viscous shock layer near the leading edge of a wing of infinite span
      
The effect of unsteady injection and wall temperature variation on the parameters of the viscous shock layer near the stagnation line of a wing of infinite span at an angle of slip is investigated on the basis of the viscous shock layer model.
      
 

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