How to find the Coefficient of Pressure (Cp) by adding function in controlDict file

badwalgurpreet · January 30, 2019, 04:16

Hi OpenFOAM Users,

I was trying to validate my NACA 0012 simulation case using OpenFOAM (Version 5.0x). I created Mesh on Pointwise and successfully run this simulation and compared results of (Coefficient of Lift and Drag ) with experimental results that I got from NAS Technical Report: NAS-2016-01.

The Inputs parameters were as follow:

(1): Free Stream Velocity = 45 m/s

(2): Mach Number = 0.13

(3): Free Stream Pressure ( (101325 pa) and Temperature (300 k )

(4): Density of air = 1.225

(5): Kinematic Viscosity = 1.4607*10^-5

(6): Reynolds Number = 3.0807 *10^6

(7): Turbulence model used: Spalart-Allmaras

I was trying to calculate the Coefficient of Pressure by adding a function in the controlDict file. I tried my best to figure it out that why I am not getting the postProcess Folder when I run this case. When I run simpleFoam in the terminal, it works fine but not producing postProcess Folder.

I am attaching the controlDict file here. Please suggest me where I am making mistake.

0.tar.gz

system.tar.gz

AlphaSierra · February 12, 2019, 02:17

Hey Gurpreet,

Have a look at this thread once. It might help.

How to calculate the pressure coefficient around an airfoil!?

Anjay

January 30, 2019, 04:16	How to find the Coefficient of Pressure (Cp) by adding function in controlDict file	#1
badwalgurpreet Member Gurpreet Singh Join Date: Jan 2017 Posts: 36 Rep Power: 9	Hi OpenFOAM Users, I was trying to validate my NACA 0012 simulation case using OpenFOAM (Version 5.0x). I created Mesh on Pointwise and successfully run this simulation and compared results of (Coefficient of Lift and Drag ) with experimental results that I got from NAS Technical Report: NAS-2016-01. The Inputs parameters were as follow: (1): Free Stream Velocity = 45 m/s (2): Mach Number = 0.13 (3): Free Stream Pressure ( (101325 pa) and Temperature (300 k ) (4): Density of air = 1.225 (5): Kinematic Viscosity = 1.460710^-5 (6): Reynolds Number = 3.0807 10^6 (7): Turbulence model used: Spalart-Allmaras I was trying to calculate the Coefficient of Pressure by adding a function in the controlDict file. I tried my best to figure it out that why I am not getting the postProcess Folder when I run this case. When I run simpleFoam in the terminal, it works fine but not producing postProcess Folder. I am attaching the controlDict file here. Please suggest me where I am making mistake. 0.tar.gz system.tar.gz

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February 12, 2019, 02:17		#2
AlphaSierra New Member Anjay Join Date: Feb 2019 Posts: 14 Rep Power: 7	Hey Gurpreet, Have a look at this thread once. It might help. How to calculate the pressure coefficient around an airfoil!? Anjay