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Typical forms of the integral curves are constructed from the results of numerical computation on a computer.
      
Numerical computation of an axisymmetric supersonic overexpanded jet of ideal gas
      
Lomonosov Computation Center of Moscow State University
      
A method based on the use of the two-approximation theory developed in [1, 2] is proposed for the computation of hypersonic flow past a conical wing with a Mach-type shock configuration.
      
Numerical values of the experimental constants are estimated in Section 3 by comparing the computation with known experimental results.
      
Approximate computation of the cavitational flow around small span wings
      
Computation of the disintegration of an asbestos-textolite surface is presented as an example.
      
The numerical computation performed for the velocity field around a body of revolution whose meridian section is a Chaplygin profile confirmed the deductions of asymptotic theory to high accuracy.
      
However, a method of straight-through computation without extraction of the compression shocks in the flow field is selected to compute the discontinuous flows.
      
Computation of the viscous shock layer on blunted cones
      
In most published papers dealing with computation of the compressible shock layer, the authors examine either the vicinity of the stagnation point or a certain region of spherical blunting [1-5].
      
Results of a computation of some hypersonic self-similar gas motions are presented.
      
Computation of the heat exchange on the spreading lines of a three-dimensional boundary layer in an inhomogeneous external strea
      
A computation method is proposed in this paper which will permit a detailed investigation of the flow structure in the jet and in the outer flow outside the separation region.
      
Analytical computation of aerodynamic characteristics of bodies of revolution under locality law conditions
      
The angles of deflection of the nose and the aerodynamic characteristics of the wing, including shunting of the free vortices shed from the side and trailing edges, are determined during the computation.
      
Computation of the gasdynamic parameters of a two-stage light-gas ballistic apparatus with deformable piston
      
The results of a computation agree satisfactorily with experimental data.
      
The results of the computation are compared with data from shock-wave observation in outer space.
      
Results are presented of a numerical computation of the elevation of the free surface and the interface caused by the application of the pressure.
      
 

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