A pure boundary integral formulation for the nonlinear equation of steady compressible nonviscous flow is given by using p Vas the dependent variable and thus the computational dimension of the problem is reduced by one.
The AUMS scheme in the form of arbitrary curvilinear coordinates is given first and then is put in conjunction with the MUSCL scheme which has third order accuracy. And then, using the implicit time marching method LU SGS, the numerical simulation of non viscous transonic and supersonic flows within the cascade with typical double circular arc blades. The calculation results presented in this paper show that they coincide well with the results published in the literature.
The two dimensional Reynolds averaged N-S equations were resolved on unstructured grids using finite volume method, the Vanleer fluxes vector splitting scheme was used for the non viscous terms, and the two layers Baldwin Lomax algebraic turbulent model was used for turbulent viscosity.
N -S方程的无粘项采用有限体积法在非结构网格上进行空间离散 ,通量分裂采用二阶精度的Vanleer格式 ,紊流粘性系数采用Bald win -Lomax二层代数紊流模型计算。
Based on the unstructured grids generated with the above function, and in combination with finite volume method, hypersonic nonequilibrium flows with chemical reactions were successfully calculated.
An implicit finite volume upwind space-marching CFD solver,i. e. Single-Sweep Parabolized Navier-Stokes Algorithm(SSPNS),is developed by integrating the PNS equations with LU-SGS method in the streamwise direction.
In [1, 2] Gonor considered the problem of imperfect inviscid gas flow about conical bodies at high supersonic speeds.
In the present paper we consider the problem of the stability of radial motion of the spherical boundary of a gas bubble in an incompressible inviscid liquid under the action of variable external pressure.
Inviscid flow past a ducted axisymmetric body with annular elliptical region
The articles [1-3] are devoted to the calculation of the radiant field and the temperature field for a given flow of a perfect inviscid nonheat-conducting radiating gas with constant absorption coefficient.
We consider the problem of steady flow of an inviscid, non-heat-conducting gas about a delta wing which is spherically blunted at the nose and cylindrlcally blunded on the leading edges, at an angle of attack.
Spreading of viscous droplets on a non viscous liquid
For this reason we propose an alternative solution, in which the topographic surface is modified in such a way that flooding it with a non viscous fluid will produce the same lakes as flooding the original relief with a viscous fluid.
These models are the non viscous fluid, the Newtonian viscous fluid, and the elastic hookean solid.
A general program using finite-difference method is written to calculate the flow field of supersonic axisymmetric nose inlet. This program is suitable to the direct problem of aerodynamic design of inlets e. g. pitot-type, single-cone, bicone, triple-cone and isentropic cone etc. Since "seperation singularity" difference method and implicit-explicit difference scheme are adopted in the calculation of inviscid flow field in the inlet, results of calculation are obtained with second order accuracy at boundary...
A general program using finite-difference method is written to calculate the flow field of supersonic axisymmetric nose inlet. This program is suitable to the direct problem of aerodynamic design of inlets e. g. pitot-type, single-cone, bicone, triple-cone and isentropic cone etc. Since "seperation singularity" difference method and implicit-explicit difference scheme are adopted in the calculation of inviscid flow field in the inlet, results of calculation are obtained with second order accuracy at boundary points and internal points, as well as near singular points. This program can offer required internal and external flow characteristics of inlets.Numerical results for five examples are in satisfactory agreement with corresponding results obtained from the method of characteristics and experimental data.
A method to calculate nonlinear compressibility effects of airfoils in subsonic flow based on the method of finite elementary solution (MFES) is presented. Using the progressive iterative, the method allows direct extension of MFES to nonlinear inviscid compressible flow. Thus it provides a new approach to the solution of the nonlinear equations.A computer program was completed in FORTRAN IV. The comparison of the results obtained with those of exact and other theoretical solutions shows superiority of this...
A method to calculate nonlinear compressibility effects of airfoils in subsonic flow based on the method of finite elementary solution (MFES) is presented. Using the progressive iterative, the method allows direct extension of MFES to nonlinear inviscid compressible flow. Thus it provides a new approach to the solution of the nonlinear equations.A computer program was completed in FORTRAN IV. The comparison of the results obtained with those of exact and other theoretical solutions shows superiority of this method to the ordinary method of finite difference, especially in the airfoil nose region.
The paper describes a numerical method for evaluation of the three-dimensional inviscid supersonic flow about the re-entry vehicles of non-symmetrical bodies. The method is devoted to determining the initial-boundary value problem for hyperbolic partial differential equations in the conservation law form. The MacCormack' s explicit finite-difference schemes with second order accuracy is adopted. For a bent sphere-cones, different oriented cylindrical coordinate systems are used in different cone regions. The...
The paper describes a numerical method for evaluation of the three-dimensional inviscid supersonic flow about the re-entry vehicles of non-symmetrical bodies. The method is devoted to determining the initial-boundary value problem for hyperbolic partial differential equations in the conservation law form. The MacCormack' s explicit finite-difference schemes with second order accuracy is adopted. For a bent sphere-cones, different oriented cylindrical coordinate systems are used in different cone regions. The computation of the body surface points is different from reference[ 1,2].The numerical examples of the bent sphere-cones and the re-entry vechicles with control flaps have been worked out to demonstrate the capability of this technique. The accuracy of the results has been examined.
无粘
inviscid
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