TY - GEN
T1 - Preliminary aerodynamic design and load calculation of a long-range eVTOL aircraft
AU - Salvador López, Noah
AU - Montoya Santamaría, Alejandro
AU - Castro, Saullo G.P.
PY - 2021
Y1 - 2021
N2 - This study presents a method for modelling the aerodynamic performance of a tandem wing long-range eVTOL aircraft at an early design stage. This procedure is applied to the design of the Wigeon eVTOL which has a tandem wing configuration with open rotor distributed propulsion. The proposed method evaluates the effect of multiple design variables on the aerodynamic performance of the eVTOL, which can then be used in multidisciplinary optimization frameworks. Firstly, the design of the wing planform is discussed, followed by the procedure for airfoil selection. Then, an analysis of the performance of the lifting surfaces is presented, in which the propeller-wing interaction and wing-wing interactions are modelled. After this the component drag method used for estimating the drag forces acting on the aircraft is discussed. An aerodynamics model used to simulate the transition flight phase of the aircraft is proposed, followed by a sensitivity analysis on relevant design variables and assumed design constants. Finally, the verification of the proposed analysis methods is outlined.
AB - This study presents a method for modelling the aerodynamic performance of a tandem wing long-range eVTOL aircraft at an early design stage. This procedure is applied to the design of the Wigeon eVTOL which has a tandem wing configuration with open rotor distributed propulsion. The proposed method evaluates the effect of multiple design variables on the aerodynamic performance of the eVTOL, which can then be used in multidisciplinary optimization frameworks. Firstly, the design of the wing planform is discussed, followed by the procedure for airfoil selection. Then, an analysis of the performance of the lifting surfaces is presented, in which the propeller-wing interaction and wing-wing interactions are modelled. After this the component drag method used for estimating the drag forces acting on the aircraft is discussed. An aerodynamics model used to simulate the transition flight phase of the aircraft is proposed, followed by a sensitivity analysis on relevant design variables and assumed design constants. Finally, the verification of the proposed analysis methods is outlined.
UR - http://www.scopus.com/inward/record.url?scp=85123422411&partnerID=8YFLogxK
U2 - 10.2514/6.2022-1331
DO - 10.2514/6.2022-1331
M3 - Conference contribution
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum
T2 - AIAA SCITECH 2022 Forum
Y2 - 3 January 2022 through 7 January 2022
ER -