The chordwise, unsteady pressure difference field for harmonically oscillating airfoils operating in the attached flow, light dynamic stall, and deep dynamic stall regimes has been modally decomposed to identify well-defined modal structures that persist across a vast parameter space of pitching parameters (i.e., reduced frequency, mean angle of attack, and oscillation amplitude). The pressure difference fields were acquired at a chord Reynolds number and Mach number of and , respectively, demonstrating results applicable to rotorcraft flight conditions. Notably, only four mode shapes were required to reconstruct the aerodynamic loads anywhere within the parameter space. Likewise, the same mode shapes showed a remarkable ability to reconstruct the aerodynamic loads of other (non-native) airfoil geometries with a similar precision. The parametric modal decomposition outlined provides a foundation to elucidate the physics of the dynamic stall phenomenon as well as reduced-order modeling techniques for the aerodynamic loading.
Parametric Modal Decomposition of Dynamic Stall
AIAA Journal ; 57 , 1 ; 176-190
01.01.2019
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Analysis of Dynamic Stall using Dynamic Mode Decomposition Technique
British Library Conference Proceedings | 2013
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