NUMERICAL STUDY OF TOTAL PRESSURE IN THE AIR INTAKE WITH SHARP EDGES APPLYING EDDY-RESOLVING SBES-METHOD
The values of the total pressure oscillations intensity root mean square parameter e in the channel of isolated air intake with sharp edges were determined as applied to industrial aerodynamics problems based on numerical solution of Navier-Stockes system of equations. Numerical solutions of Navier-Stockes system of equations were obtained using eddy­resolving Stress Bkended Eddy Simulation (SBES) approach employing ANSYS CFX solver. Simulation of the 3D flowing of the viscous compressible gas around and inside the object was performed employing spatial regular multi-shell grid. The procedure of computational grid generation was being performed in manual mode employing ICEM CFD software. To evaluate fidelity of the computational study based on SBES method application, comparison of the obtained values of the root-mean square parameter of pulsations intensity with experimental data was performed. The data processing procedure herewith was conducted in concordance with the standard experimental technique approved in TsAGI. Numerical simulation results are presented in the form of plots of parameter e values in the engine section as a function of the specific reduced air flow q (λ <sub>en</sub> ) through the engine cross section. The air intake duct throttling was modelled by cross-clamping of the auxiliary duct in the form Laval nozzle. The auxiliary duct wall profile in the longitudinal section herewith was constructed using the Vitoshinsky formula. The article performed a comparison of total pressure oscillations obtained while computational study in monitored points of the metering cross­section with oscillograms obtained while experimental study according to readings of the total pressure pulsations sensors, installed on the model at the same points of the reference cross-section. The parameter e values obtained in the framework of this work in the engine cross-section for the air intake and engine synchronization mode in all regarded range of of the incoming flow Mach numbers M = 0-1.8 (at zero angles of attack and sideslip) are in good agreement with the experimental data. Maximum discrepancy between computational and experimental results was (Dε)<sub>max</sub> = 1% in absolute units of the e parameter. The e parameter values were obtained for both the air intake configuration without a boundary layer control system, and the one with a boundary layer control system.