Receptivity to Freestream Acoustic Noise in Hypersonic Flow over a Generic Forebody

CERMINARA, Adriano, DURANT, Antoine, ANDRÉ, Thierry, SANDHAM, Neil D and TAYLOR, Nigel J (2018). Receptivity to Freestream Acoustic Noise in Hypersonic Flow over a Generic Forebody. Journal of Spacecraft and Rockets, 56 (2), 447-457.

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Direct numerical simulations of the Navier–Stokes equations have been performed to investigate the receptivity and breakdown mechanisms in a Mach 6 flow over a generic forebody geometry with freestream acoustic disturbances. The simulations are based on transition experiments carried out in April 2015 in the Boeing/U.S. Air Force Office of Scientific Research Mach 6 facility at Purdue University. A three-dimensional model for both fast and slow freestream acoustic waves with multiple frequencies and spanwise wave numbers has been adopted in the numerical simulations, for which high-amplitude disturbances have been considered in order to simulate noisy wind-tunnel conditions. The numerical results revealed similarities in comparison to the experimental observations, especially when slow acoustic waves were considered as freestream disturbances. In particular, slow acoustic waves have been found to induce the breakdown process via crossflow instabilities located in the off-centerline region, with formation of streamwise streaks. Fast acoustic waves, in contrast, appeared more efficient in inducing earlier nonlinear growth through destabilization of the boundary layer along the symmetry plane of the body.

Item Type: Article
Uncontrolled Keywords: 0901 Aerospace Engineering; 0913 Mechanical Engineering; Aerospace & Aeronautics; 4001 Aerospace engineering
Identification Number:
Page Range: 447-457
SWORD Depositor: Symplectic Elements
Depositing User: Symplectic Elements
Date Deposited: 26 Jul 2023 15:08
Last Modified: 11 Oct 2023 13:01

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