Aeroacoustics of NACA 0018 airfoil with a cavity

Garret C.Y. Lam, Randolph C.K. Leung

Research output: Journal article publicationJournal articleAcademic researchpeer-review

9 Citations (Scopus)


This paper reports a detailed numerical study of the aeroacoustics of a NACA 0018 airfoil with acavity at zero angle of attack, with chord-based Reynolds and freestream Mach numbers at 2 × 104 and 0.2, in two dimensions. For an airfoil without a cavity, vortex shedding from the trailing edge and low-frequency wake flapping are found to be the major aeroacoustic processes. The presence of a cavity introduces additional acoustic generation due to cavity oscillation modes but weakens the noise sourceatthe airfoil trailing edge viaajittering of the flow. Three aeroacoustic mechanisms are identified with extensive fast Fourier transform, wavelet, and coherence analyses. The airfoil with cavity effectively increases the lift-to-drag ratio from almost zero (ordinary airfoil) to approximately 5.3. However, it radiates less acoustic power by 1.2 and by 2.6 dB from the airfoil upper and lower surfaces, respectively, even if the acoustic contribution of wake flapping of the ordinary airfoil is excluded. The outcomes of the study suggest that an airfoil with a cavity is a feasible configuration that gives high lift-to-drag ratio yet low noise generation, making it a promising quiet airfoil design at low Reynolds number.

Original languageEnglish
Pages (from-to)4775-4786
Number of pages12
JournalAIAA Journal
Issue number12
Publication statusPublished - Dec 2018

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering
  • Acoustics and Ultrasonics
  • Computational Mechanics

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