XFLR5 Aerodynamic & Load Analysis

Budget: €30 - €250

Aerodynamic, Stability and Structural Load Analysis (XFLR5)

I am seeking a detailed aerodynamic and structural analysis of a light aircraft wing and horizontal stabilizer using XFLR5.

1. Input Data

I will provide:

• Wing and tail geometry (DAT/XFLR5 file)
• Mass distribution and CG locations
• Flight condition matrix (angles of attack, airspeeds, altitudes)
• Predefined operating points in spreadsheet format

2. Flight Conditions

The analysis shall cover:

• Maximum speed: 230 km/h at 2000 m altitude
• Cruise speed: 190 km/h at 2000 m altitude
• Stall speed: 83 km/h at 100 m altitude

Angles of attack will be defined in the supplied dataset.

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3. Aerodynamic Analysis

Run XFLR5 simulations and provide:

• Lift coefficient (CL), drag coefficient (CD), and moment coefficient (CM)
• Full polars for each flight condition
• Clear plots and exported raw data (CSV format)

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4. Load Distribution & Structural Outputs

Using the aerodynamic results, derive:

• Spanwise lift distribution
• Shear force distribution
• Bending moment distribution
• Torsional moment distribution

Outputs must include:

• Plots (clear and labeled)
• Raw numerical data (CSV)
• Consistent units suitable for structural sizing

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5. Stability Analysis

Perform a full stability analysis including:

Static Stability

• Longitudinal stability (Cm vs α)
• Lateral-directional stability indicators

Dynamic Stability (all four modes)

• Short period
• Phugoid
• Dutch roll
• Spiral

Evaluate stability at:

• 230 km/h
• 190 km/h
• 83 km/h

Include:

• Stability derivatives
• Eigenvalue analysis (if applicable)
• Interpretation of aircraft response

Also include a brief discussion noting that not all four modes are typically stable simultaneously.

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6. Control Surface Analysis

Run additional simulations with elevator deflections:

• −25°
• +25°

Provide:

• Resulting pitching moment coefficients
• Impact on trim and stability

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7. Horizontal Stabilizer Loads (Composite Structure)

Using the aerodynamic results, determine loads acting on the horizontal stabilizer:

• Lift distribution
• Root bending moment
• Shear forces
• Torsional loads

These results will be used for composite structural sizing, so accuracy and clarity are critical.

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8. Deliverables

• Complete Word report including:

• Methodology

• Results

• Plots and explanations

• All raw data in CSV format

• Clearly organized outputs ready for structural calculations

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9. Notes

• The XFLR5 model already includes:

• Geometry

• Masses

• CG positions

• Elevator fixed tilt: −3.0°

• If any input data is missing or inconsistent, please flag it before running simulations.

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Please confirm your approach before starting and briefly describe how you will handle:

• Load scaling vs AoA recomputation
• Stability derivative extraction
• Conversion of aerodynamic outputs into structural loads