Estimated Cd0 at low Reynolds numbers based on rotor measurements
Published: 1 July 2026| Version 1 | DOI: 10.17632/98cmncxnvf.1
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Description
Estimated Cd0 values of the NACA 4-digits airfoils and flat plates at low Reynolds numbers (16,800 to 56,000) were shown based on rotor measurements. The experimental data were the result of work from an accepted article. The detailed method was shown in the article: Hikaru Otsuka, Haruto Yoshimoto, Riki Takayama, Hiroshi Tokutake, Zero-lift drag estimation of symmetrical airfoils at low Reynolds numbers based on rotor experiments, Flow Measurement and Instrumentation, 2026. https://doi.org/10.1016/j.flowmeasinst.2026.103464
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Institutions
- Kanazawa UniversityIshikawa, Kanazawa
Categories
Fluid Mechanics, Aerospace, Aerodynamics, Rotorcraft, Propeller
Funders
- Japan Society for the Promotion of ScienceMinistry of Education, Culture, Sports, Science and TechnologyTokyoGrant ID: JP24K17207