Aerodynamic Analysis of a Prandtl-D Inspired Tailless UAV with Fuselage and Elevon Integration
Faculty Mentor Information
Dr. Vibhav Durgesh, University of Idaho
Presentation Date
7-16-2026
Abstract
This investigation focuses on the aerodynamic analysis of a Prandtl-inspired tailless unmanned aerial vehicle (UAV) configuration using OpenVSP and the VSPAERO vortex-lattice solver. Two configurations were studied: a baseline Prandtl-D3C wing and a modified Prandtl-D3C UAV with an integrated fuselage, landing gear, and elevon control surfaces. Aerodynamic simulations were performed over a range of angles of attack to evaluate lift, drag, aerodynamic efficiency, and stability-related trends for both configurations.
The results were analyzed to determine how the addition of practical aircraft components affected the aerodynamic behavior of the Prandtl-inspired wing. The modified configuration preserved the main aerodynamic characteristics of the Prandtl-D3C concept while introducing additional drag and changes in pitching moment behavior due to the added fuselage, landing gear, and control surfaces. Despite these changes, the aircraft maintained key features associated with Prandtl-inspired span loading and tailless UAV design.
This study demonstrates that a Prandtl-inspired wing can be adapted toward a more practical UAV configuration while retaining important aerodynamic advantages. Future work will include comparison with a traditional UAV configuration to quantify differences in lift generation, aerodynamic efficiency, and payload capability, followed by wind tunnel testing, prototype fabrication, and flight-test validation.
Aerodynamic Analysis of a Prandtl-D Inspired Tailless UAV with Fuselage and Elevon Integration
This investigation focuses on the aerodynamic analysis of a Prandtl-inspired tailless unmanned aerial vehicle (UAV) configuration using OpenVSP and the VSPAERO vortex-lattice solver. Two configurations were studied: a baseline Prandtl-D3C wing and a modified Prandtl-D3C UAV with an integrated fuselage, landing gear, and elevon control surfaces. Aerodynamic simulations were performed over a range of angles of attack to evaluate lift, drag, aerodynamic efficiency, and stability-related trends for both configurations.
The results were analyzed to determine how the addition of practical aircraft components affected the aerodynamic behavior of the Prandtl-inspired wing. The modified configuration preserved the main aerodynamic characteristics of the Prandtl-D3C concept while introducing additional drag and changes in pitching moment behavior due to the added fuselage, landing gear, and control surfaces. Despite these changes, the aircraft maintained key features associated with Prandtl-inspired span loading and tailless UAV design.
This study demonstrates that a Prandtl-inspired wing can be adapted toward a more practical UAV configuration while retaining important aerodynamic advantages. Future work will include comparison with a traditional UAV configuration to quantify differences in lift generation, aerodynamic efficiency, and payload capability, followed by wind tunnel testing, prototype fabrication, and flight-test validation.