RCAIDE.Library.Methods.Noise.Frequency_Domain_Buildup.Rotor.TBL_TE_broadband_noise
TBL_TE_broadband_noise#
- TBL_TE_broadband_noise(f, r_e, L, U, M, R_c, Dbar_h, Dbar_l, R_delta_star_p, delta_star_p, delta_star_s, alpha_star)[source]#
This computes the turbument boundary layer- trailing edge noise compoment of broadband noise using the method outlined by the Brooks, Pope and Marcolini (BPM) Model
- Assumptions:
BPM models assumes a naca 0012 airfol
- Source:
BPM Model: Brooks, Thomas F., D. Stuart Pope, and Michael A. Marcolini. Airfoil self-noise and prediction. No. L-16528. 1989.
- Inputs:
R_delta_star_p - Reynolds number correlated to boundary layer thicness [m] delta_star_p - boundary layer thickness of pressure side [m] delta_star_s - boundary layer thickness of suction side [m] R_c - Reynolds number [-] alpha_star - angle of attack blade section [deg] delta_p - boundary layer of pressure section [m L - length of blade section [m] U - velocity of blade section [m/s] M - Mach number [-] c - airfoil section chord [m] f - frequency spectrum [Hz] Dbar_h - high frequency directivity term [-] Dbar_l - low frequency directivity term [-] r_e - distance from noise source to observer [m]
- Outputs
SPL_TBL_TE - Sound pressure level of turbument boundary layer [dB]
- Properties Used:
N/A