Challenge

Week 7 - Minor Project

Aim: To analyze the NACA 0012 profiles for various angles of Attack for both compressible & Incompressible flow.

Abstract:

1. C-domain is created around the NACA-0012 airfoil.

2. Structured mesh is created for both compressible and incompressible flows for a Y+ of 2,3 respectively.

3. Velocity Inlet, Pressure outlet, wall & Pressure-Farfield boundary conditions are used.

4. Cd, Cl values are computed and contour plots are made.

Case-settings & Boundary Conditions:

Domain Created for Incompressible Flow

Mesh:

Case Settings & Boundary Conditions

pressure-based, Absolute Steady State solver is used.

K-w SST model is the viscous model.

The working fluid is Air with Density - 2.131 Kg/m3 & viscosity of 1.7894e-05 Kg/ms

For boundary Conditions

We have velocity inlet, pressure outlet, symmetry, and wall for the airfoil.

Velocity has been provided as components based on the angle of attack

For Incompressible Flow: V = 52.15 m/s

For Compressible Flow: V = 272 m/s

for compressible flow the sided of the domain will be applied with pressure far-field.

Results:

INCOMPRESSIBLE CASE

ANGLE OF ATTACK -5 Degrees:

Velocity & Pressure contour plots for the 5-degree angle of attack are shown.

ANGLE OF ATTACK -10 Degrees:

ANGLE OF ATTACK -15 Degrees:

COMPRESSIBLE FLOW

ANGLE OF ATTACK - 5 DEGREE

ANGLE OF ATTACK - 10 DEGREE

ANGLE OF ATTACK - 15 DEGREE

The numerical values of Cd & Cl for all angles of attack for both the flow regime are shown below:

Ship work like this
in your own course.