XFLR5 Aerodynamic & Load Analysis
Budget: €30 – €250 EUR
## 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.
---
## 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)
---
## 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
---
## 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.
---
## 6. Control Surface Analysis
Run additional simulations with **elevator deflections**:
* −25°
* +25°
Provide:
* Resulting pitching moment coefficients
* Impact on trim and stability
---
## 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.
---
## 8. Deliverables
* Complete **Word report** including:
* Methodology
* Results
* Plots and explanations
* All raw data in **CSV format**
* Clearly organized outputs ready for structural calculations
---
## 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.
---
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
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.
---
## 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)
---
## 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
---
## 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.
---
## 6. Control Surface Analysis
Run additional simulations with **elevator deflections**:
* −25°
* +25°
Provide:
* Resulting pitching moment coefficients
* Impact on trim and stability
---
## 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.
---
## 8. Deliverables
* Complete **Word report** including:
* Methodology
* Results
* Plots and explanations
* All raw data in **CSV format**
* Clearly organized outputs ready for structural calculations
---
## 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.
---
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