In this work, numerical simulations are conducted to investigate the effects of Reynolds () and Mach () numbers on thrust characteristics for a pitching airfoil. The results show that as increases, the thrust performance is improved. The inverse square root of Reynolds number is demonstrated to be a universal scaling law for both thrust coefficients and drag-to-thrust crossovers across and . In contrast, as increases above 0.1, the thrust performance is significantly reduced, especially when approaches 0.3. The thrust coefficients follow the square law of the Mach number, which also exhibits universality. Furthermore, the incompressible vortex projection method and the compressible vortex projection method are employed for thrust decomposition. Before this, the full expression of the compressible vortex projection method is derived. It is revealed that as increases, the improvement of thrust performance is primarily attributed to the reduced flow viscous effect and, meanwhile, benefits from the formation of more intense boundary layers and vortex structures in near wake. As increases, the enhancement of local flow compressibility ultimately leads to the divergence of added mass drag and thereby reduces the thrust performance.
Reynolds and Mach Number Effects on Propulsive Performance for a Pitching Airfoil
AIAA Journal ; 62 , 12 ; 4711-4731
2024-12-01
Article (Journal)
Electronic Resource
English
Multielement Airfoil Performance due to Reynolds and Mach Number Variations
Online Contents | 1993
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