Back to Search
Start Over
Aerodynamic Design Consideration for Stability of a Lightweight Solar-Powered Aircraft
- Source :
- Traektoriâ Nauki, Vol 8, Iss 5, Pp 4010-4016 (2022)
- Publication Year :
- 2022
- Publisher :
- Altezoro s.r.o. (Slovak Republic) and Publishing Center "Dialog" (Ukraine), 2022.
-
Abstract
- Aerodynamic design analysis was conducted for the stability of a lightweight solar aircraft weighing 3 kg and a wingspan of 3.2 m. Airfoil analysis was conducted on four selected airfoils. The following factors were considered: good aerodynamic characteristics, low Reynolds number, high lift, low drag, high lift-to-drag ratio, quiet moment coefficient, moderate thickness, and camber curvature. WE-3.55.93 airfoil was selected as best and used to design the wing, and NACA 0008 was used to develop the empennage. The fuselage was designed with two compartments 1.9 m long, and the second compartment is made of aluminium or carbon fibre to reduce weight. The first compartment was 0.95 m long and 0.4 m in diameter. The centre of gravity was determined for the importance of the various aircraft components to ensure aerodynamic stability and balance. The complete assembly was designed using XFLR5 v6 software.
Details
- Language :
- English, Russian, Ukrainian
- ISSN :
- 24139009
- Volume :
- 8
- Issue :
- 5
- Database :
- Directory of Open Access Journals
- Journal :
- TraektoriĆ¢ Nauki
- Publication Type :
- Academic Journal
- Accession number :
- edsdoj.7da16bdde8184dca927f07f36795c4bd
- Document Type :
- article
- Full Text :
- https://doi.org/10.22178/pos.81-10