Search - inviscid

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[matlab] hw-nozzle DL : 0: 求解二维无粘欧拉方程，算的是一个二维收扩喷管-Solving two-dimensional inviscid Euler equations, operator of a collection of two-dimensional expansion nozzle
Update : 2025-04-04 Size : 6kb Publisher : 李超
[Algorithm] 88 DL : 1: C语言实现二维无粘欧拉方程的求解，采用二阶迎风MUSCL格式，求解二维收扩喷管，计算时间比MATLAB少很多-C Language Implementation of two-dimensional inviscid Euler equations, using second-order upwind MUSCL format, solving two-dimensional expansion nozzle closed, the computation time much less than the MATLAB
Update : 2025-04-04 Size : 259kb Publisher : 李超
[Windows Develop] simple3 DL : 0: 本程序是用fortran言语编写的三维SIMPLE算法程序，针对不可压、无粘流体。-This procedure is used to prepare three-dimensional fortran language SIMPLE algorithm procedures, for incompressible, inviscid fluid.
Update : 2025-04-04 Size : 6kb Publisher : Anthonymary2008
[Applications] 1 DL : 0: 采用偏微分方程数值解法生成翼型O型网格并采用速度势方程求低速不可压无粘流场 -Numerical solution of partial differential equations using Airfoil O-grid generation and use low-speed velocity potential Equation incompressible inviscid flow field
Update : 2025-04-04 Size : 2kb Publisher : wangwei
[matlab] EFFECTS DL : 0: 本文应用重叠网格技术对子母弹分离过程中多体无粘超声速流动进行了数值仿真。采用 NND 格式,通过求解Euler 方程,给出了母弹附近的子弹气动干扰特性。-In this paper, separation of overlapping grid of cluster bombs during the multi-body inviscid supersonic flow of the numerical simulation. With NND format, by solving the Euler equations, the mother is given a bullet shells near the aerodynamic characteristics.
Update : 2025-04-04 Size : 313kb Publisher : 王顺红
[Other] maccomack_1d DL : 0: 一维Riemann问题，即激波管问题，是一个典型的一维可压缩无黏气体动力学问题，并有解析解。对它采用二阶精度MacCormack两步差分格式进行数值求解。同时，为了初学者入门和练习方便,这里给出了用Fortran77语言编写的计算一维Riemann问题的计算程序，供大家学习参考。——计算流体力学教程-One-dimensional Riemann problem, that shock tube problem is a typical one-dimensional compressible inviscid gas dynamics, and analytical solution. Its second order accuracy MacCormack two-step numerical solution of difference scheme. Meanwhile, for beginner and practice convenience, here are written using Fortran77 one-dimensional Riemann problem of the calculation of the calculation procedures for them to learn information.- Computational Fluid Dynamics Course
Update : 2025-04-04 Size : 2kb Publisher : 沉默的囧羊
[Communication-Mobile] ausm-euler0012 DL : 0: this fortran code can be used for analyse Inviscid flow over naca0012 airfoil with C_type grid. this code is developed by AUSM+ method.
Update : 2025-04-04 Size : 3kb Publisher : kiarash
[Algorithm] Euler_solver DL : 0: 基于有限体积法的naca0012翼型的无粘绕流计算-Calculation of airfoils based on the finite volume method naca0012 inviscid flow around
Update : 2025-04-04 Size : 317kb Publisher : 戴得志
[Other] 2D_euler DL : 0: 求解流场二维无粘欧拉方程，中心差分，人工耗散-Solving the flow field in two-dimensional inviscid Euler equation, central difference, artificial dissipation
Update : 2025-04-04 Size : 4.21mb Publisher : 朱正
[Other] MOC_NOzzle3D DL : 0: computer program for the calculation of steady three dimensional adiabatic flows in supersonic rocket engine nozzles. The fluid is assumed to be an inviscid perfect gas and the flow is assumed to be shock free. The governing equations for this flow model consist of the continuity equation, the momentum equations, and the speed of sound equation. The steady three dimensional supersonic flows is computed using a pentahedral bicharacteristic method. An inverse marching method based on the network of wavelines and the pathline is employed. The spline surface fit is used in the iteration procedure to evaluate the location of the unknown point in the new reference plane and its flow properties-computer program for the calculation of steady three dimensional adiabatic flows in supersonic rocket engine nozzles. The fluid is assumed to be an inviscid perfect gas and the flow is assumed to be shock free. The governing equations for this flow model consist of the continuity equation, the momentum equations, and the speed of sound equation. The steady three dimensional supersonic flows is computed using a pentahedral bicharacteristic method. An inverse marching method based on the network of wavelines and the pathline is employed. The spline surface fit is used in the iteration procedure to evaluate the location of the unknown point in the new reference plane and its flow properties
Update : 2025-04-04 Size : 5.09mb Publisher : AALI
[Other] The-one-dimensional-Riemann-problem DL : 0: 一维Riemann问题，即激波管问题，是一个典型的一维可压缩无黏气体动力学问题，并有解析解。对它采用二阶精度MacCormack两步差分格式进行数值求解。同时，为了初学者入门和练习方便,这里给出了用语言和编写的计算一维Riemann问题的计算程序，供大家学习参考。-The one-dimensional Riemann problem, namely the shock tube problem is a typical one-dimensional compressible inviscid gas dynamics, and analytical solutions. It solved numerically using second-order accuracy MacCormack two-step difference scheme. Convenient for beginner and exercises given here to the calculation procedure of the one-dimensional Riemann problem with the calculation of language and writing, for all to learn.
Update : 2025-04-04 Size : 166kb Publisher : 李轩
[matlab] pablo_4kth DL : 0: Potential flow around Airfoils with Boundary Layer coupled One-way (Pablo) is a pedagogical low-speed airfoil analysis program written in MATLAB. It uses a one way coupled inviscid + boundary layer model.
Update : 2025-04-04 Size : 71kb Publisher : jes2012
[Algorithm] RKDG-Euler DL : 1: 使用龙格-库塔间断Galerkin方法（RKDG）求解无粘流动Euler方程的程序，适用于计算流体力学RKDG方法的学习和研究。-Using the discontinuous Galerkin method (DG) for solving inviscid flow Euler equations procedures applicable to DG methods of study and research.
Update : 2025-04-04 Size : 609kb Publisher :
[Energy industry] 5 DL : 0: 计算流体力学中，渐缩渐扩管的无粘与可压缩流动的模拟-Computational Fluid Dynamics in-divergent tube inviscid compressible flow simulation study with numerical examples
Update : 2025-04-04 Size : 4.21mb Publisher : 李明
[transportation applications] Matlab-Mach-3-blow-a-cylinder DL : 0: 3马赫气流吹拂圆柱体，二维非结构化网格，网格自适应优化，Matlab代码，无粘-Mach 3 airflow blowing cylinder, two-dimensional unstructured grids, adaptive mesh optimization, Matlab code, inviscid
Update : 2025-04-04 Size : 3.03mb Publisher : Bush
[Algorithm] Sod_exact DL : 0: 一维无粘可压缩欧拉方程求解激波管问题-One-dimensional inviscid compressible Euler equations shock tube problem. . .
Update : 2025-04-04 Size : 2kb Publisher : 王小平
[Mathimatics-Numerical algorithms] vkt_airfoil_v3 DL : 0: Karman-Trefftz airfoil is an intriguing airfoil for which a complete set of exact solutions can be computed. This solution has been used by many people to verify the accuracy of their inviscid code (incompressible limit). If you have not, use this code now to generate a (quadrilateral or triangular) grid, run your code on it, compute the error, and verify the accuracy of your code. Me? I have used it for my third-order multigrid Cauchy-Riemann solver
Update : 2025-04-04 Size : 6kb Publisher : ARP
[transportation applications] liman DL : 0: 一维问题，即激波管问题，是一个典型的一维可压缩无黏气体动力学问题，并有解析解。对它采用二阶精度两步差分格式进行数值求解。-One-dimensional problem, namely shock tube problem is a typical one-dimensional compressible inviscid gas dynamics problems, and analytical solutions. It uses a two-step difference scheme of second order accuracy of the numerical solution.
Update : 2025-04-04 Size : 2kb Publisher : panda
[transportation applications] Lax-Webdroff2D DL : 0: 斜激波在平面刚壁上反射问题是具有解析解的二维可压缩无黏流动问题。对它采用具有二阶精度两步差分格式进行数值求解-Oblique shock reflection problem in the plane wall is just a two-dimensional analytical solution of compressible inviscid flow problems. It has a second order accuracy using a two-step numerical solution of differential formats
Update : 2025-04-04 Size : 3kb Publisher : panda
[Other] SU2 Wiki · inviscid GitHub DL : 0: how to inviscid bump in a chanell
Update : 2025-04-04 Size : 880kb Publisher : Lord_Light

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