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Numerical and experimental investigation of airfoil derived from peregrine FALCON
- Source :
- Measurement: Sensors, Vol 31, Iss , Pp 100956- (2024)
- Publication Year :
- 2024
- Publisher :
- Elsevier, 2024.
-
Abstract
- In this work, the Peregrine falcon's airfoil is derived and is analysed numerically and experimentally in a non-flapping, non-morphing case. The airfoil is analysed numerically using a Steady State RANS k-ω SST model at different Reynolds numbers with ANSYS Fluent solver and is compared with NACA 23015 and NACA 64–210. The numerical method of approach is validated at a high Reynolds number of 1x106 experimentally. The results dictate that FALCON airfoil has a cl, max that is 54 % and 118 % higher than NACA 23015 and NACA 64–210 respectively. Stalling at 12oangle of attack, the airfoil generates an (LD) of 84, and produces positive lift coefficients till -5o angle of attack. The cl of FALCON is higher than the NACA 64–210 and 23015 at all angles of attack. The variation of (LD) with AoA is smooth and of a parabolic nature than an abrupt one.
Details
- Language :
- English
- ISSN :
- 26659174
- Volume :
- 31
- Issue :
- 100956-
- Database :
- Directory of Open Access Journals
- Journal :
- Measurement: Sensors
- Publication Type :
- Academic Journal
- Accession number :
- edsdoj.bccfa775a33410b882322b700a5ab3f
- Document Type :
- article
- Full Text :
- https://doi.org/10.1016/j.measen.2023.100956