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Aim: To do the Flow simulation over a NACA 0017 Airfoil in SolidWorks Objective: To create the wing section needed for SolidWorks Flow Simulation Insert the curve of NACA 0017 airfoil Create the extruded model of Airfoil Setting up a Flow Simulation project for external flow To run the calculations for various Angle…
Keval Patel
updated on 28 Feb 2022
Aim: To do the Flow simulation over a NACA 0017 Airfoil in SolidWorks
Objective:
Flow of the project:
Terms used in Airfoil:
Figure 1 Basic figure and terms of airfoil
Chord: A chord is defined as the distance betweem the leading edge, which is the point at the front of the airfoil and has maximum curvature. while the trailing edge is the point at the rear of the airfoil with maximum curvature along the chord line.
Chord line: A chord line is the straight line connecting the leading and trailing edges.
Pitching moment: The moment or torque produced by the aerodynamic force on the airfoil.
Aerodynamic center: is the chord-wise length about which the pitching moment is independent of lift coefficient and angle of attack (AOA) at this centre.
Center of pressure is the chord-wise length about which pitching moment is zero.
Angle of attack: The angle formed between a refernce line on a body and the incoming flow.
Upper surface: the upper surface is also known as the suction surface, associated with high velocity and low static pressure.
Lower surface: The lower surface is aslo known as the pressure surface with high static pressure.
Figure 2 shows the overview of forces acting on an airplane
Figure 3 indicates the reaction forces acting on a single airfoil in an airplane wing
What is NACA?
NACA: NATIONAL ADVISORY COMMITTEE OF AERONAUTICS
NACA is now NASA: NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
Nomenclature of NACA 4-digit series:
CASE:1 (Angle of Attack – 0 degree)
Steps for modelling of Airfoil:
Insert > Curve > Curve through XYZ points
Figure 4 Extruded model of NACA 0017 Airfoil
Figure 5 Configurations were used to create the different Angle of Attack (AOA)
Figure 6 Body-Move/copy feature was used for changing the Angle of Attack (AOA)
Steps for Flow simulation study:
Computational Domain Settings:
The size of computational domain is generally taken as 5 times the chord from the leading edge and 10-15 times the chord from the trailing edge.
Goals:
Surface goals:
Figure 8 Shows the Face selection for surface goal
Meshing:
Figure 9 Indicates the mesh settings for simulation study
Automatic settings have been selected
Figure 10 Batch Run Selection procedure
This flow simulation was performed using the Batch Run feature in SolidWorks.
Results of Case-1 (Angle of Attack – 0 degree)
Cut plot of Velocity contour:
Figure 11 Cut plot of Velocity contour
Figure 12 Detailed view of Cut plot of velocity contour
Cut Plot of Pressure contour:
Figure 13 Cut plot of pressure contour
Figure 14 Detailed view of cut plot of pressure contour
Drag Force graph:
Figure 15 Graph of drag force vs no. of iterations
Lift Force graph:
Figure 16 Graph of lift force vs no. of iterations
Figure 17 Results of Lift force and Drag force
Figure 18 Convergence of Drag Force was achieved at iteration number-189 while the Lift force failed to converge.
Results of Case-2 (Angle of Attack – 2 degree)
Cut plot of velocity
Figure 19 Cut plot of Velocity contour
Figure 20 Detailed view of Cut plot of velocity contour
Cut plot of pressure:
Figure 21 Cut plot of pressure contour
Figure 22 Detailed view of Cut plot of pressure contour
Drag force graph:
Figure 23 Graph of drag force vs no. of iterations
Lift Force graph:
Figure 24 Graph of lift force vs no. of iterations
Figure 25 Results of Lift force and Drag force
Results of Case-3 (Angle of Attack – 4 degree)
Cut plot of velocity
Figure 26 Cut plot of Velocity contour
Figure 27 Detailed view of Cut plot of velocity contour
Cut plot of pressure:
Figure 28 Cut plot of pressure contour
Figure 29 Detailed view of Cut plot of pressure contour
Drag force graph:
Figure 30 Graph of drag force vs no. of iterations
Lift Force graph:
Figure 31 Graph of lift force vs no. of iterations
Figure 32 Results of Lift force and Drag force
Results of Case-4 (Angle of Attack – 6 degree)
Cut plot of velocity
Figure 33 Cut plot of Velocity contour
Figure 34 Detailed view of Cut plot of velocity contour
Cut plot of pressure:
Figure 35 Cut plot of pressure contour
Figure 36 Detailed view of Cut plot of pressure contour
Drag force graph:
Figure 37 Graph of drag force vs no. of iterations
Lift Force graph:
Figure 38 Graph of lift force vs no. of iterations
Figure 39 Results of Lift force and Drag force
Results of Case-5 (Angle of Attack – 8 degree)
Cut plot of velocity
Figure 40 Cut plot of Velocity contour
Figure 41 Detailed view of Cut plot of velocity contour
Cut plot of pressure:
Figure 42 Cut plot of pressure contour
Figure 43 Detailed view of Cut plot of pressure contour
Drag force graph:
Figure 44 Graph of drag force vs no. of iterations
Lift Force graph:
Figure 45 Graph of lift force vs no. of iterations
Figure 46 Results of Lift force and Drag force
Results of Case-6 (Angle of Attack – 10 degree)
Cut plot of velocity
Figure 47 Cut plot of Velocity contour
Figure 48 Detailed view of Cut plot of velocity contour
Cut plot of pressure:
Figure 49 Cut plot of pressure contour
Figure 50 Detailed view of Cut plot of pressure contour
Drag force graph:
Figure 51 Graph of drag force vs no. of iterations
Lift Force graph:
Figure 52 Graph of lift force vs no. of iterations
Figure 53 Results of Lift force and Drag force
Goal | 0 Deg AOA | 2 Deg AOA | 4 Deg AOA | 6 Deg AOA | 8 Deg AOA | 10 Deg AOA |
Drag Force [N] (Average Values) | 13.912 | 14.424 | 15.155 | 16.221 | 17.528 | 19.526 |
lLift Force [N] (Average values) |
-0.030 | 6.785 | 13.276 | 20.135 | 26.237 | 32.723 |
Figure 54 Comparison of Lift force and Drag force at various angle of attack 0,2, 4, 6, 8, 10
Conclusion:
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Aim: To do the Flow simulation over a NACA 0017 Airfoil in SolidWorks Objective: To create the wing section needed for SolidWorks Flow Simulation Insert the curve of NACA 0017 airfoil Create the extruded model of Airfoil Setting up a Flow Simulation project for external flow To run the calculations for various Angle…
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