A Theoretical Basis for the Scaling Law of Broadband Shock Noise Intensity in Supersonic Jets

<table>Dependence of acoustic response to vorticity waves incident on a Mach 8 shock (solid lines: linear theory, circles from nonlinear Euler simulations; from Zang et al. [<a href="/journals/aav/2011/573209/#B28">28</a>]).</table>

Advances in Acoustics and Vibration

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Figure 6

Figure 6: A Theoretical Basis for the Scaling Law of Broadband Shock Noise Intensity in Supersonic Jets 