Aim : Model the flow over a NACA0017 Airfoil for the angle of attack 0,2,4,6,8,10 Compare the lift anddrag force.
Introduction : The NACA Airfoil are Airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word "NACA". The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties.
In my case according to create project in NACA0017 Airfoil which data file is download from official website of airfoiltools.com
Procedure :
1.) first to import data file in solidwork and convert in to entity.
2.) adjust angle for requirement from 0 to 10 degree and the convert in to solid part.
3.) create wizard for external simulation and use time dependent.
4.) use air as fluid flow 600 m/s in x direction.
5.) remain use default .
6.) convert computational domain in 2D and adjust according to flow.
7.) use global goal (Normal force in (X) and (Y)) direction and friction force in (x) and (y) direction.
8.) also use surface goal for friction forces in (x) and (y) direction.
9.) use basic and local mesh in the surface.
10.) and the RUN the program.
11.) after completion calculation over result is obtained in result column.
12.) add cut plot for velocity and arrange colour bar for 200 shades of colour.
13.) now we have obtained simulation result for lift and drag force with different colour range.
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