Acoustic Leading-Edge Receptivity for Supersonic/Hypersonic Flows over a Blunt Wedge

CERMINARA, Adriano and SANDHAM, Neil D (2017). Acoustic Leading-Edge Receptivity for Supersonic/Hypersonic Flows over a Blunt Wedge. AIAA Journal, 55 (12), 4234-4244.

AIAAJ_2017_Acoustic Leading-Edge Receptivity for Supersonic-Hypersonic Flows over a Blunt Wedge.pdf - Accepted Version
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Leading-edge receptivity to fast and slow acoustic waves of boundary layers on a cylinder–wedge geometry is investigated for a set of six different cases with Mach number ranging from 3.0 to 7.3, through direct numerical simulations of the Navier–Stokes equations. The structure of the disturbance field transmitted downstream of the shock by the imposed freestream waves is analyzed, as well as the characteristics of the wall response and its sensitivity to the angle of attack and the freestream-wave inclination angle. The results show that different postshock wave structures are formed for fast and slow acoustic waves, consisting of high-amplitude dragged and reflected waves for the fast-wave case and of low-amplitude convected waves for the slow-wave case. A good agreement is found with linear interaction theory. The wall response for fast waves shows a strong resonant amplification of mode F in the nose region and a modulated long-wavelength behavior farther downstream. In contrast, the response to slow waves shows an initial decay in the leading-edge region and an overall lower amplitude. The simulation results enable freestream disturbances, which are difficult to measure directly in experiments, to be related to wall pressure fluctuations.

Item Type: Article
Uncontrolled Keywords: 0901 Aerospace Engineering; 0905 Civil Engineering; 0913 Mechanical Engineering; Aerospace & Aeronautics; 4001 Aerospace engineering; 4012 Fluid mechanics and thermal engineering
Identification Number:
Page Range: 4234-4244
SWORD Depositor: Symplectic Elements
Depositing User: Symplectic Elements
Date Deposited: 24 Aug 2023 15:25
Last Modified: 11 Oct 2023 12:16

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