I HAVE WRITTEN A 2D EULER SOLVER

gchnhn · April 30, 2008, 00:01

HI

I HAVE WRITTEN A 2D UNSTRUCTURED EULER SOLVER. IT USES TRIANGULAR MESH, READS THE MESH IN COBALT FORMAT, WRITES THE OUTPUT IN TECPLOT CELL-CENTERED FORMAT.

IT CAN DEAL WITH ONLY 2 BOUNDARY TYPES AS OF NOW- FARFIELD AND WALL. SCHEME USED IS ROE'S SCHEME. I HAVE RUN IT OVER A NUMBER OF TEST CASES AND FOUND SATISFACTORY RESULTS.

COULD SOMEONE TELL ME IF IT CAN BE OF ANY HELP TO CFD-ONLINE.COM? DO U SUGGEST SUBMITTING IT TO THIS SITE?

PRAPANJ

April 30, 2008, 00:19

Hi

which TEST CASES have you solved....??

cfdxue

April 30, 2008, 15:15

Well,

I have solved, 1. subsonic flow over RAE2822 airfoil, transonic airfoil 2. transonic flow over the same 3. flow over wedge(15 degree) (oblique shock) 4. prandtl meyer expansion over 15 degree convex corner

May 1, 2008, 02:53

If you used the explicit time-stepping, then your code is of the same category as NSC2KE open code by B. Mohammadi. If the time-stepping is implicit, then your code might be of interest to CFD community indeed.

May 4, 2008, 07:03

Nowadays, I am also solving test cases. I have solved following test cases:

1. rearward step,

2. blunt body and

3. compression corner 7.5 degree

all are high supersonic.

I am interested to solve your test case 3 & 4. may you please provide me their reference.

I am using Harten-Yee TVD and ACM schemes.

we may compare our results with experimental data and could make some conclusion.

Hoping positive response from you.

cfdxue

crazy · August 11, 2011, 08:21

hii...i have just started to learn cfd....i need a 2D euler eqn solver..plz post if u hv one

panou · August 13, 2011, 07:11

Which method do you use in your code? Finite volume?

If you use finite volume without reconstruction technique , you have first order accuracy. Therefore if you want to take more accurate results you must do very dense mesh in high gradient regions. Also you haven't problem with shock capturing due to the monotonicity of all first order schemes.

seyedashraf · August 15, 2011, 03:32

Quote:

Originally Posted by cfdxue
;55001

Nowadays, I am also solving test cases. I have solved following test cases:

1. rearward step,

2. blunt body and

3. compression corner 7.5 degree

all are high supersonic.

I am interested to solve your test case 3 & 4. may you please provide me their reference.

I am using Harten-Yee TVD and ACM schemes.

we may compare our results with experimental data and could make some conclusion.

Hoping positive response from you.

cfdxue

it seems like your numerical method is FVM
am I wrong?
I'm very interested in TVD schemes and would like to utilize it in different numerical methods.
If you both were cfd-online users we would exchange some Experiments etc

gchnhn · September 27, 2011, 13:55

plz send me a copy and your detailed deduction process
tx a lot

gchnhn@gmail.com

ljnpu · October 26, 2011, 08:17

Would you please send me a copy?
I am a new learner who is writing a 2D EULER SOLVER.
I use the Finite Volume method,and Jameson's central scheme
But I have some questions in farfield boundary conditions.
Many thanks!
ljnpu@foxmail.com

LBMer_Young · October 26, 2011, 08:41

Would you please send me a copy?
I apply the hybrid FVM-LBM to solve the Euler equations, but i have some troubles in the computation of the gradients in boundary.
Thank you very much!
229344870@qq.com

ljnpu · October 26, 2011, 09:15

Quote:

Originally Posted by prapanj
;54954

HI

I HAVE WRITTEN A 2D UNSTRUCTURED EULER SOLVER. IT USES TRIANGULAR MESH, READS THE MESH IN COBALT FORMAT, WRITES THE OUTPUT IN TECPLOT CELL-CENTERED FORMAT.

IT CAN DEAL WITH ONLY 2 BOUNDARY TYPES AS OF NOW- FARFIELD AND WALL. SCHEME USED IS ROE'S SCHEME. I HAVE RUN IT OVER A NUMBER OF TEST CASES AND FOUND SATISFACTORY RESULTS.

COULD SOMEONE TELL ME IF IT CAN BE OF ANY HELP TO CFD-ONLINE.COM? DO U SUGGEST SUBMITTING IT TO THIS SITE?

PRAPANJ

Would you please send me a copy?
I am a new learner who is writing a 2D EULER SOLVER.
I use the Finite Volume method,and Jameson's central scheme
But I have some questions in farfield boundary conditions.
Many thanks!
ljnpu@foxmail.com

illuminati5288 · January 31, 2012, 15:33

Hello,

I am coding a 2D euler code with Roe flux in a turbine blade passage. The roe flux on its own works perfectly (specifying a single left and single right state). however when implemented in the turbine blade solver and looping over the edges of a cell, the residuals go to NaN..

Could you please tell me why this happens/

Thx

April 30, 2008, 00:01	I HAVE WRITTEN A 2D EULER SOLVER	#1
prapanj Guest Posts: n/a	HI I HAVE WRITTEN A 2D UNSTRUCTURED EULER SOLVER. IT USES TRIANGULAR MESH, READS THE MESH IN COBALT FORMAT, WRITES THE OUTPUT IN TECPLOT CELL-CENTERED FORMAT. IT CAN DEAL WITH ONLY 2 BOUNDARY TYPES AS OF NOW- FARFIELD AND WALL. SCHEME USED IS ROE'S SCHEME. I HAVE RUN IT OVER A NUMBER OF TEST CASES AND FOUND SATISFACTORY RESULTS. COULD SOMEONE TELL ME IF IT CAN BE OF ANY HELP TO CFD-ONLINE.COM? DO U SUGGEST SUBMITTING IT TO THIS SITE? PRAPANJ gchnhn and ljnpu like this.

April 30, 2008, 00:19	Re: I HAVE WRITTEN A 2D EULER SOLVER	#2
cfdxue Guest Posts: n/a	Hi which TEST CASES have you solved....?? cfdxue

April 30, 2008, 15:15	Re: I HAVE WRITTEN A 2D EULER SOLVER	#3
prapanj Guest Posts: n/a	Well, I have solved, 1. subsonic flow over RAE2822 airfoil, transonic airfoil 2. transonic flow over the same 3. flow over wedge(15 degree) (oblique shock) 4. prandtl meyer expansion over 15 degree convex corner

May 1, 2008, 02:53	Re: I HAVE WRITTEN A 2D EULER SOLVER	#4
A.K. Guest Posts: n/a	If you used the explicit time-stepping, then your code is of the same category as NSC2KE open code by B. Mohammadi. If the time-stepping is implicit, then your code might be of interest to CFD community indeed.

May 4, 2008, 07:03	Re: I HAVE WRITTEN A 2D EULER SOLVER	#5
cfdxue Guest Posts: n/a	Nowadays, I am also solving test cases. I have solved following test cases: 1. rearward step, 2. blunt body and 3. compression corner 7.5 degree all are high supersonic. I am interested to solve your test case 3 & 4. may you please provide me their reference. I am using Harten-Yee TVD and ACM schemes. we may compare our results with experimental data and could make some conclusion. Hoping positive response from you. cfdxue

August 11, 2011, 08:21	Need a 2D euler solver	#6
crazy New Member Rohit Join Date: Aug 2011 Posts: 1 Rep Power: 0	hii...i have just started to learn cfd....i need a 2D euler eqn solver..plz post if u hv one

August 13, 2011, 07:11		#7
panou New Member aaaaaaaaaaaaaa Join Date: Apr 2011 Posts: 23 Rep Power: 3	Which method do you use in your code? Finite volume? If you use finite volume without reconstruction technique , you have first order accuracy. Therefore if you want to take more accurate results you must do very dense mesh in high gradient regions. Also you haven't problem with shock capturing due to the monotonicity of all first order schemes.

September 27, 2011, 13:55	I need your code to study	#9
gchnhn New Member Guo Qinghua Join Date: Sep 2011 Location: Nanjing Posts: 10 Rep Power: 2	plz send me a copy and your detailed deduction process tx a lot gchnhn@gmail.com

October 26, 2011, 08:17		#10
ljnpu New Member liujie Join Date: Oct 2011 Posts: 6 Rep Power: 2	Would you please send me a copy? I am a new learner who is writing a 2D EULER SOLVER. I use the Finite Volume method,and Jameson's central scheme But I have some questions in farfield boundary conditions. Many thanks! ljnpu@foxmail.com

October 26, 2011, 08:41	I need your code for study	#11
LBMer_Young New Member L.M. Yang Join Date: Oct 2011 Posts: 6 Rep Power: 2	Would you please send me a copy? I apply the hybrid FVM-LBM to solve the Euler equations, but i have some troubles in the computation of the gradients in boundary. Thank you very much! 229344870@qq.com

January 31, 2012, 15:33	2d Euler turbine blade passage	#13
illuminati5288 New Member Vignesh Suresh Join Date: Jul 2011 Posts: 10 Rep Power: 2	Hello, I am coding a 2D euler code with Roe flux in a turbine blade passage. The roe flux on its own works perfectly (specifying a single left and single right state). however when implemented in the turbine blade solver and looping over the edges of a cell, the residuals go to NaN.. Could you please tell me why this happens/ Thx

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