Large eddy simulation of the aeroacoustic environment of a rocket fairing

The implicit large eddy simulation (ILES) method based on the fifth-order weighted essentially non-oscillatory (WENO) scheme is proposed to resolve the unsteady turbulent flow around the fairing wall at Ma=0.8. The root-mean-square of the fluctuating pressure coefficient distribution and the power spectral density at several locations are presented to compare with wind tunnel data and reference's results, demonstrating this method is promising for engineering application with relatively coarse meshes. When the transonic flow passes the corner, it gets separated and interacted with shock waves, resulting in a server fluctuation-pressure level and lower frequency vibration. In the end, the deficiencies of the empirical formulas are denoted and corresponding improvements are proposed based on the results of ILES.