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Fixed Wing: Flow Analysis

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Target Aircraft Information​

  • Name: ONERA-M6 Wing
  • Wing span: 0.212[m]
  • Reference area (main wing area): 0.8878[m^2]
  • Reference length (mean aerodynamic chord, MAC): 0.6397[m]

Download Sample STEP File​

Download the sample STEP file to follow along with this tutorial:

Sample CAD File

📦 Download ONERA-M6.step

Step 1: Import CAD Geometry​

Figure 1. Import CAD

  1. Navigate to the Flow Analysis module
  2. Click the Import CAD button
  3. Select the ONERA-M6.step file
  4. Verify that the import completed successfully

Important Notes

  • Geometry is directly reflected in the analysis without modification
  • Ensure proper scale and units before importing

Step 2: Configure Flow Domain​

Figure 2. Flow Domain Setup

Set up sufficient flow space to properly capture flow characteristics.

  1. Flow Domain Center: <1000, 0, 0>
  2. Flow Domain Size: <10000, 5000, 5000>
  3. Pitch Angle: 10[DEG]
  4. Reference Area and Length: Configure as follows
    • Reference Area: 0.8878[m^2]
    • Reference Length: 0.6397[m]

Step 3: Configure Simulation Settings and Run​

Figure 3. Simulation Settings

3.1. Simulation Settings​

  • Flow Velocity: 50[m/s]
  • Simulation Accuracy: 5
  • Other settings: Use defaults

After configuring simulation settings, verify that the mesh has been generated as shown in the figure.

Step 4: Run Analysis​

Set the number of cores freely and run the analysis. For the given CAD, it is recommended to use 8 or more cores.

If the analysis runs successfully, residuals information will appear.

Step 5: Visualize Results​

Figure 4. Result Visualization

Result visualization is primarily used to review whether the flow analysis results are physically reasonable. In this analysis, we mainly examine the following phenomena:

  • Wing tip vortex generation
  • Wake formation behind the geometry
  • Stagnation point occurrence
  • Pressure distribution on the aircraft

Step 6: Review Reports​

6.1. Aerodynamic Performance Analysis: Key Performance Indicators and Analysis Conditions​

Figure 5. Report: Key Performance Indicators

  • Check lift coefficient (CL) and drag coefficient (CD)
  • Verify that flow characteristics and simulation settings match the configured information

6.2. Aerodynamic Performance Analysis: System Forces and Moments​

Figure 6. Report: Forces and Moments

Review the forces acting on the entire aircraft.

  • Fx, Fy, Fz: Forces in x, y, z directions [N]
  • Mx, My, Mz: Moments about x, y, z axes [N·m]

Design Insights:

  • Verify lift coefficient (CL) is within appropriate range
  • Minimize drag coefficient (CD) for efficient design
  • Check stability of pitching moment (My)
  • Review whether wing tip vortex is not excessive

Aircraft Design Tips and Troubleshooting​

1) If Lift is Insufficient​

  • Increase angle of attack
  • Increase wing area
  • Select high-lift airfoil
  • Consider adding flaps or slats

2) If Drag is Excessive​

  • Optimize wing shape
  • Design streamlined fuselage
  • Reduce surface roughness
  • Reduce induced drag with winglets

3) If Aircraft Stability is Problematic​

  • Adjust center of gravity (CG) position
  • Adjust horizontal/vertical tail size
  • Review wing position
  • Adjust dihedral angle

4) CAD Import Failure​

  • Solution: Verify STEP file format is correct, check file size and complexity

5) Analysis Takes Too Long​

  • Solution: Optimize flow domain size, adjust mesh resolution, increase number of cores

6) Results Appear Unrealistic​

  • Solution: Check Reynolds number, review boundary conditions

7) Convergence Issues​

  • Solution: Adjust mesh resolution

Need Assistance or Have Questions?

Frequently Asked Questions: FAQ Link

Support Inquiries: support@everysim.io