Synthesis of the Aerodynamic Model of a Flying Wing Aircraft

Conference Paper (2025)
Author(s)

S. Asaro (TU Delft - Flight Performance and Propulsion)

R Vos (TU Delft - Flight Performance and Propulsion)

Research Group
Flight Performance and Propulsion
DOI related publication
https://doi.org/10.2514/6.2025-0852
More Info
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Publication Year
2025
Language
English
Research Group
Flight Performance and Propulsion
ISBN (electronic)
978-1-62410-723-8
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Abstract

Flying wing aircraft, such as the Flying-V considered in this study, can substantially contribute to reducing the carbon footprint of the aviation sector. To enable adequate predictions regarding performance, stability, and control, a validated aerodynamic model of the Flying V is important. In this paper, the aerodynamic model of the Flying V is derived. The first part of the paper compares the aerodynamic coefficients determined with experiments and simulations conducted on a subscale version of the aircraft. The experiments are conducted in a wind tunnel, and with flight tests, the simulations are conducted using the vortex lattice method (VLM), panel method, and Reynolds-averaged Navier-Stokes (RANS) equations. The comparison highlights the dependency of the aerodynamic coefficients from the angle of attack, which influences the flow acting on the aircraft. Based on the outcome of the comparison for the subscale aircraft, the aerodynamic model of the full-scale aircraft is derived by combining RANS and VLM simulations. All the aerodynamic coefficients are derived as a function of the angle of attack and different Mach numbers and altitudes.

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