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  1. Home/
  2. Mohamed Fuadh/
  3. Flow Simulation using SolidWorks-Flow over an airfoil

Flow Simulation using SolidWorks-Flow over an airfoil

Introduction The aim of this challenge is to model the flow over a NACA0017 airfoil for the angle of attacks 0,2,4,6,8,10 compare the lift and drag forces. Procedure The X,Y,Z plot points can be found out online from the given website.It is copied into the txt file in a certain format.It is put in the curves option in…

    • Mohamed Fuadh

      updated on 23 Jun 2019

    Introduction

    The aim of this challenge is to model the flow over a NACA0017 airfoil for the angle of attacks 0,2,4,6,8,10 compare the lift and drag forces.

    Procedure

    The X,Y,Z plot points can be found out online from the given website.It is copied into the txt file in a certain format.It is put in the curves option in solidworks to plot the points.

    The required angle of attach is setup in certain plane.

    The curve is made a solid using the extrude option. This makes it an airfoil.

    The flow simulation is setuup during which time the flow velocity as well as bounding box,goals,mesh etc are all setup. 

    The simulation is run and  iterations are run until a solution is converged upon.

    The values are recorded. 

    Results

    Here the lift  forces are along y axis and drag forces are along y axis.

     

    Case 1: 0 Degree Angle of Attack.

    Lift and Drag Forces

    As expected there is negligible lift as the angle of attack is 0.

    Pressure and Velocity

     

    Case 2: 2 degree angle of Attack

     

     Lift And Drag

    Pressure And Velocity

     

    Case 3: 4 degree Angle of Attack

     

    Lift and Drag

    Pressure and Velocity

     

    Case 4:6 Degree angle of attack

     

    Lift and Drag

     

    Pressure and Velocity

     

    Case 5: 8 Degrees Angle of Attack

     

     

     Lift and Drag

    Pressure and Velocity

     

    Case 6: 10 Degree Angle of Attack

     

    Lift and Drag Forces

    Pressure and Velocity

    Conclusions

    1: The lift increases as the angle of attack increases. Ther is negligible lift at 0 degree angle of attack.

    2:The drag increases as the angle of attack increases

    3: The minimum pressure experienced by the airfoil decreases as the angle of attack     increases. No obvious relation in the case of maximum pressure.

    4: More high velocity air flows through the top of the airfoil as expected to generate required lift as the angle of attack increases.

    5: Similiarly the low pressure region is also at the top of the airfoil as the angle of attack increases to generate the required lift.

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