Numerical method to compute acoustic scattering effect of a moving source.
In this paper, the aerodynamic characteristic of a ducted tail rotor in hover has been numerically studied using CFD method. An analytical time domain formulation based on Ffowcs Williams-Hawkings (FW-H) equation is derived for the prediction of the acoustic velocity field and used as Neumann boundary condition on a rigid scattering surface. In order to predict the aerodynamic noise, a hybrid method combing computational aeroacoustics with an acoustic thin-body boundary element method has been proposed. The aerodynamic results and the calculated sound pressure levels (SPLs) are compared with the known method for validation. Simulation results show that the duct can change the value of SPLs and the sound directivity. Compared with the isolate tail rotor, the SPLs of the ducted tail rotor are smaller at certain azimuth.
School of Aeronautic Science and Engineering, Beihang University, Beijing, 100191 People's Republic of China.
Hao
H
Song
School of Aeronautic Science and Engineering, Beihang University, Beijing, 100191 People's Republic of China.
Mingxu
M
Yi
School of Aeronautic Science and Engineering, Beihang University, Beijing, 100191 People's Republic of China.
Jun
J
Huang
School of Aeronautic Science and Engineering, Beihang University, Beijing, 100191 People's Republic of China.
Yalin
Y
Pan
School of Aeronautic Science and Engineering, Beihang University, Beijing, 100191 People's Republic of China.
Dawei
D
Liu
Acoustic velocity; Aerodynamic characteristic; Aerodynamic noise; Boundary element method; Ducted tail rotor