2D Implicit Unstructured Euler code (OSSANEuler2DImplicit; 5 files):
data_package_v0.f90
euler_solver_v0.f90
jacobian_v0.f90
linear_solve_v0.f90
main_v0.f90
readme_v0.txt
twod_bump_irregular_grid_v0.f90(grid generation code)
Want to learn how to write an implicit unstructured CFD code? Grab this code,
look inside to see how it is written, get good understanding, and then write your own.
This code computes a steady flow over a bump with the Roe flux by two solution
methods: explicit 2stage RungeKutta scheme and implicit (defect correction) method with
the Jacobian exact for 1storder scheme, on irregular triangular grids.
A grid generation code is included.
NOTE: It is an edgebased secondorder finitevolume code. It contains enough information to convert it to a cellcentered finitevolume code.
NOTE: These files are different from the explicit version of the OSSANEuler2D (which is designed to solve a shock diffraction problem).
NOTE: The implicit method becomes Newton's method with infinte CFL and GS relaxations
for 1storder spatial discretization (if LSQ gradients are set zero).
[ I plan to upload a 2D NavierStokes code (OSSAN2D) in future. This is the inviscid steady version. ]


Machine zero:
machinezero_v2.f90
What is machine zero? Maybe, it is a nonzero number which cannot be
recognized by a machine.
So, it depends on machines. Download, compile, and run it
to find out the `zero' in your machine.
Generalized. Now it finds `machine zero' for a given value. (112912)


Automatic Differentiation Ver.1:
ad_driver_v1.f90
module_ddt3.f90
Automatic differentiation is nice. It is sometimes used to compute
flux Jacobians for implicit formulaitons in CFD. To those who are curious about it,
here is a set of files with which you can experience and learn how it works.
Simply compile the file "ad_driver.f90" and run it (the other file will be automatically included
in the program) to get a feeling of automatic differentiation.


Numerical Fluxes (3D Euler) Ver.3:
threed_euler_fluxes_v3.f90
Here are 3D Euler numerical fluxes. Download and take a look. Learn
how the standard Roe and a very robust rotatedhybrid fluxes are implemented
for the 3D Euler equations, and also how the Roe flux can be implemented without tangent vectors.
Included are Roe with/without tangent vectors, and RotatedRHLL fluxes.
I'll be extremely happy if you kindly report bugs. Thank you, arigatou!
Bugs fixed for the RHLL flux, more comments added, Roe without tangent vectors added. (043012).


2D Explicit Unstructured Euler code (OSSANEuler2D; 3 files):
data_package_v0.f90
euler_solver_v0.f90
main_v0.f90
readme_v0.txt
twod_rectangular_grid_v0.f90
Want to learn how to write an unstructured CFD code? Grab this code,
look inside to see how it is written, get good understanding, and then write your own.
This code has Roe and RotatedRHLL fluxes, Van Albada limiter, and a 2stage RungeKutta
timestepping for solving a shock diffraction problem. It works for quadrilateral grids,
triangular grids, and mixed grids also. It is set up to solve a shock diffraction problem.
You can easily modify it for solving other problems. A grid generation code is included.
NOTE: It is an edgebased finitevolume code. It contains enough information to convert it to a cellcentered finitevolume code.
[ I plan to upload a 2D NavierStokes code (OSSAN2D) in future. This is the inviscid version. ]


3D Grid Generation for Hemishpere Cylinder:
How to make a nice and isotropic 3D grid for a hemisphere cylinder?
I came up with an idea and implemented it into the code. It works great.
It still requires a little improvement, but it does generate a very
nice triangulation on the
body. Grab the code, try it, improve it and let me know. Thanks, arigatou!
121811: Serious bug found. Will correct them and upload it again.


Flow around a KarmanTrefftz airfoil (generate grids and exact solutions):
vkt_airfoil_v3.f90
,
vkt_airfoil_v1_display.m
KarmanTrefftz 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 thirdorder multigrid CauchyRiemann
solver (IJNMF
2004).
Updated (101310). Formula corrected. It works now for cambered airfoils.


1D Hyperbolic Diffusion Scheme:
oned_upwind_diffusion.f90
Believe or not, the diffusion equation is solved by an upwind scheme.
The idea is to integrate an equivalent hyperbolic system toward
a steady state. This way, we can advance in time with a large
O(h) time step (not O(h^2)), and compute the solution gradient
with the equal order of accuracy. Compare with a common scheme (Galerkin)
for 512 nodes to see how fast the upwind scheme can be.
Reference: JCP2007  Preprint


3D Mixed Grid Generation:
mixgrid_cube_v3.f90
Mixed (tetrahedralprismatic) grid in a unit cube is generated and written in the UGRID
format. Learn how a typical viscoustype grid can be generated.
You may want to modify the code to apply stretching to the prismatic layer for
a smooth transition to the isotropic tetrahedral region.


3D Tetrahedral Grid Generation:
tetgrid_cube_v3.f90
Tetrahedral grid in a unit cube is generated and written in the UGRID
format. Learn how the hexahedron can be divided into six tetrahedra.
Mdify the code to divide the hexahedron into five tetrahedra.


3D Prismatic Grid Generation:
przgrid_cube_v3.f90
Prismatic grid in a unit cube is generated and written in the UGRID format.
It's just a cubic domain, but may be useful in learning unstructured grid data.


3D Hex Grid Generation (Unstructured Format):
hexgrid_cube_v3.f90
Hexahedral grid in a unit cube is generated and written as
unstructured/finiteelement data in a UGRID 3D unstructured grid file.
It may be useful for those who want to learn a typical data structure of
unstructured grids.


Genetic Algorithm, Ver.1:
ga_v1.f90
This is a simple genetic algorithm program for finding
minimizers of a function. I wrote this in 1999 when I was interested
in aerodynamic optimization problems. I think that genetic algorithm is
a very interesting optimization algorithm.


1D Euler Code Ver.1:
oned_euler_v1.f90
,
oned_euler_plot_v1.m
Here is a 1D Euler code (1D shock tube code) for solving Sod's shock tube problem, using
Roe's Approximate Riemann solver, minmod limiter, and 2stage RungeKutta
timestepping. Learn how a secondorder nonoscillatory Euler code is written,
or just run it to see how it is capable of computing discontinuous solutions.
Incorporate various flux subroutines given below to explore other methods.
Minor bugs fixed (122910).


Numerical Fluxes (1D Euler) Ver.5:
oned_euler_fluxes_v5.f90
All numerical fluxes are functions of the left and right states (and
possibly dt and dx). Learn how those famous fluxes can be
implemented, or just use them to see how they work for various shocktube problems.
Included are LaxFriedrichs, Richtmyer, MacCormack,
StegerWarming, Van Leer, AUSM, ZhaBilgen, Godunov, Osher, Roe, Rusanov,
HLL, HLLL, AUFS flux functions.
Bug fixed for Godunov fluxes.


Numerical Fluxes (2D Euler) Ver.2:
twod_euler_fluxes_v2.f90
Want 2D fluxes also? Here you are. Download and take a look. Learn
how the standard Roe and a very robust rotatedhybrid fluxes are implemented.
Included are Roe and RotatedRHLL fluxes (Riemann Solvers).
Bugs fixed for the RotatedRHLL flux. It works very well now.


Ringleb's Flow (generate grids and exact solutions):
ringleb_v1.f90
Ringleb's flow is a famous exact solution of the compressible
Euler equations with a smooth transition from subsonic to supersonic
without any shock waves. This solution has been used actually by many people to verify the accuracy
of their Euler code. If you have not, use this code now to generate a (quadrilateral
or triangular) grid, run your Euler code on it, compute the error, and verify
the accuracy of your Euler code.
Minor bugs fixed (122910).


Blasius solutions for a flow over a flatplate (compute the exact solution) :
blasius_v1.f90
,
blasius_plot_v1.m
Exact solution for a flow over a flatplate.
This solution has been used by many people to verify the accuracy
of their NavierStokes code. If you have not,
use this code now to compute the exact solution at any point
on your grid, compute the error, and verify
the accuracy of your code.
Minor bugs fixed (122910).


Viscous shock structure NSsolution (compute the exact solution) :
ns_shock_structure_v1.f90
,
ns_shock_structure_plot_v1.m
Exact solution for a shock wave internal structure to the 1D NavierStokes
equations. This solution has been used by some people to verify the accuracy
of their 1D NavierStokes code. If you have not,
use this code now to generate a data file for the exact solution, use it
as an initial solution for your code, converge to a steady state, and
verify the accuracy of your code.
Minor bugs fixed (122910).

