Scaled Model of VTOL Aircraft for Wind Tunnel Testing
Conducting theoretical and experimental analysis of a scaled VTOL aircraft through aerodynamic modeling and wind-tunnel testing.
CAD model of the wing with the Krueger flap panels deployed, vortex generators on the upper surface, and the vented motor nacelle at midspan.
Wing with the center section hidden, showing the carbon-fiber spar rods, the motor mount and nacelle at midspan, and the Krueger flap servos.
Krueger actuation linkage at the end rib. The servo turns the hinge rod through a two-link arm to deploy the Krueger flap.
ANSYS velocity-contour simulation at 120 knots and a 20-degree angle of attack.
Close-up of the velocity magnitude through the deployed Krueger flap slot.
Velocity vectors at the Krueger slot, showing the air accelerating through the gap and curling around the leading edge.
ANSYS static-pressure contour simulation at 120 knots and a 0-degree angle of attack.
Velocity magnitude on the centreline slice through the nacelle and rotor, showing the propeller accelerating the flow over the wing.
Velocity vectors on a slice through the Krueger flap and vortex generators, showing the flow turning around the leading edge.
3D ANSYS CFD of the full wing tunnel model at 120 knots and 0 degrees angle of attack, showing pressure coefficient on the wing, Krueger flap, vortex generators and nacelle.
Velocity magnitude on planes 20 mm and 90 mm behind the trailing edge, showing the wake and the rotor slipstream from the 4x7 propeller.
Wiring diagram.
For my senior capstone, our three-person team is developing a scaled model of a VTOL aircraft for wind tunnel testing. We used XFOIL and NeuralFoil to analyze and compare candidate airfoil shapes, focusing on a high lift-to-drag ratio. We then used ExBEMT, a MATLAB-based Extended Blade Element Momentum Theory solver, to calculate the propeller size and blade pitch that would produce the maximum thrust for the design. Finally, we used ANSYS to validate the aerodynamic performance of the selected airfoil across multiple angles of attack, both with and without high-lift devices.
I created the CAD model around a 1900 KV 4-pole BLDC motor and incorporated a load cell to measure the thrust produced by the motor and propeller system. Engineering calculations were performed to size the drone motor and determine the required power supply. The model will be 3D printed, and the wing will feature carbon-fiber rods for structural reinforcement. The vortex-generator panels are interchangeable, allowing us to test and compare different vortex-generator configurations. We plan to acquire and analyze the load-cell data using NI CompactDAQ and LabVIEW. The completed model will be tested at 120 knots in the university's wind tunnel, allowing us to compare experimental measurements with our aerodynamic predictions.
The project is currently in progress, and this page will be updated as the design, analysis, manufacturing, and testing continue.
Technologies & Tools
Project Details
Category
Capstone
Year
2026