A variety of tools, from fundamental to high order, have been used to better understand applications of distributed electric propulsion to aid the wing and propulsion system design of the Leading Edge Asynchronous Propulsion Technology (LEAPTech) project and the X-57 Maxwell airplane. Three high-fidelity, Navier-Stokes computational fluid dynamics codes used during the project with results presented here are FUN3D, STAR-CCM+, and OVERFLOW. These codes employ various turbulence models to predict fully turbulent and transitional flow. Results from these codes are compared for two distributed electric propulsion configurations: the wing tested at NASA Armstrong on the Hybrid-Electric Integrated Systems Testbed truck, and the wing designed for the X-57 Maxwell airplane. Results from these computational tools for the high-lift wing tested on the Hybrid-Electric Integrated Systems Testbed truck and the X-57 high-lift wing presented compare reasonably well. The goal of the X-57 wing and distributed electric propulsion system design achieving or exceeding the required ?? (sub L) = 3.95 for stall speed was confirmed with all of the computational codes.
Comparison of High-Fidelity Computational Tools for Wing Design of a Distributed Electric Propulsion Aircraft
2017
22 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Test Facilities & Equipment , Fluid Mechanics , Computational fluid dynamics , Wings , Aircraft design , Electric propulsion , Computer programs , Turbulence models , Turbulent flow , Systems integration , Navier-stokes equation , Transition flow , Aerodynamic stalling , Ground tests