Result and discussion in the plot of an elliptical

Result and Discussion
In the plot of an Elliptical, the Grid lines have been smoothed out due to the elliptic
equations, eliminating extreme jaggedness resulting from the algebraic grid. This would
ensure a more accurate flow model.
Enter the number of grid points in the i direction: 50
Enter the number of grid points in the j direction: 50
The solution took 2434 iterations to converge.
Elliptic grid over an Airfoil
Overall, an elliptic grid was shown to provide desired results for discretization. It succeeded
in smoothing out otherwise rough edges created through algebraic grid generation. At the
same time, the algebraic grid provided a suitable starting point for the generation of the
elliptic grid.
0 0.5 1 1.5
x
2 2.5 3

Dept of ANE CA Lab Manual
MRCET 18
EXPERIMENT 5
FLOW OVER AN AEROFOIL
Aim: To simulate flow over NACA 0012 airfoil and find pressure velocity distribution
over airfoil.
Problem description : Consider air flowing over NACA 0012 airfoil. The free stream velocity
is 90 m/s
Assume standard sea-level values for the free stream
properties: Pressure = 101,325 Pa
Density = 1.2250 kg/m
3
Temperature = 288.16 K
Kinematic viscosity v = 1.4607e-5 m
2
/s
Software:
ICEM and CFX
Steps Involved In ICEM
1) Creation of Geometry in ICEM CFD:
 Importing the Aerofoil coordinates
File →Import Geometry→Formatted point data→Select the file of aerofoil
coordinates which is in DAT format→ok. Now the coordinates will be displayed.
 Geometry→Create/modify curve→From points→Select above points and leave
last 2 points→middle click
 Similarly on bottom side
 Join the end points of the curves
 Create a point in z direction using Geometry →create point→Explicit
coordinate→x=0,y=0,z=1→Apply.
 Join points (0,0,0) and (0,0,1) using create/modify curves→from points.
 Create/Modify surfaces→curven driven→driving select curve along z axis →driven
curves select airfoil→Apply
2) Creation of Domain:
 Geometry →Create/Modify surface →Satndard shapes→Box→X Y Z = 7 2
1→Origin= -3 -1 0 →Apply
 Geometry →Create/Modify surface →Segment/Trim surface →Select surface →side
walls of box →Select curves → airfoil curves →Apply
 Create Body→Part:body→Material point→Location→centroid of 2 points→2
screen location→select 2 points in box such that its center will be above or below

Dept of ANE CA Lab Manual
MRCET 19
airfoil→Apply
3) Creation of parts:
 Parts in the tree→Righ t click→Create part
Part Suction → Select entity airfoil upper surface
Part: Pressure → Select entity airfoil lower
surface
Part: TE → Select entity airfoil rear surface
Part : Inlet→ Select entity box front face
Part : Outlet→Select entity box back face
Part: Walls→ Select entity remaining box
walls
4) Generation of Mesh:
 Mesh→Global M esh setup → Max Element
size:1 → Curvature?Proximity Based Refinement →Enabled→Min size:
0.01 →Apply.
 Part Mesh Setup
Inlet→Maximum size : 0.2
Outlet→Maximum size: 0.2
Walls→Maximum size: 0.2

Dept of ANE CA Lab Manual
MRCET 20
Suction and Pressure→Maximum size:0.05