Flying testbed for propellers
In this project, we design an aircraft for testing propellers in flight.
To test various propellers on the same small aircraft (that essentially is, to control the aircraft's drag), we will use split flaps.
What is ready:
Next steps:
To test various propellers on the same small aircraft (that essentially is, to control the aircraft's drag), we will use split flaps.
What is ready:
- design code (full aircraft general aerodynamic design and analysis, as well as matching the flap deflection angle and propeller diameter)
- uncertainty propagation analysis
Next steps:
- I want to try and print this aircraft from a combination of TPU LW and PLA LW, and still trying to find the correct settings for printing
- 3D model of the aircraft for printing
- Printing, wiring, tuning the autopilot, flight tests
The most important result so far is this relationship between the diameter of the propeller to be tested, the corresponding flap deflection angle, and the flight speed
In addition, we explored the uncertainty propagation to estimate the expected accuracy of propeller performance measurements.
A Monte Carlo uncertainty analysis was conducted to propagate manufacturing, measurement, test condition, and processing errors into propeller thrust and power predictions. At nominal conditions (0.254 m diameter, 15° pitch, 6000 RPM, 15 m/s), thrust exhibited a 1σ relative uncertainty of 4.7%, while power uncertainty was significantly lower at 2.6%. Test conditions - particularly airspeed and density variations - were the dominant uncertainty contributors, overshadowing manufacturing and sensor errors. Sensitivity analysis identified blade pitch, diameter, and airspeed as the most critical parameters affecting thrust.
A parametric sweep further revealed that low-speed, small - diameter test points suffer from thrust uncertainties as high as 12%, suggesting that higher speed conditions yield more reliable performance measurements.
A Monte Carlo uncertainty analysis was conducted to propagate manufacturing, measurement, test condition, and processing errors into propeller thrust and power predictions. At nominal conditions (0.254 m diameter, 15° pitch, 6000 RPM, 15 m/s), thrust exhibited a 1σ relative uncertainty of 4.7%, while power uncertainty was significantly lower at 2.6%. Test conditions - particularly airspeed and density variations - were the dominant uncertainty contributors, overshadowing manufacturing and sensor errors. Sensitivity analysis identified blade pitch, diameter, and airspeed as the most critical parameters affecting thrust.
A parametric sweep further revealed that low-speed, small - diameter test points suffer from thrust uncertainties as high as 12%, suggesting that higher speed conditions yield more reliable performance measurements.
