Numerical simulation of the flowfield around helicopter engine inlet

To obverse the flow field of a helicopter engine inlet, the finite volume method was adopted and Navier-Stokes (N-S) equation was solved by generating the body-fitted structural grid. The low speed and hovering flight of MI-171 helicopter were numerically simulated, and the flow field characteristic around engine inlet of this helicopter was calculated. Following this, beginning with the prescribed wake model, a semi-empirical correction for the vortex core effect on rotor wake was made and a free wake model was adopted, this method was also used to calculate the flow field characteristic around the engine inlet of this helicopter. From the calculated results paralleling to the engine line and verticalizing to it on engine inlet showed that these two different methods can predict the vortex wake flow field distribution around the helicopter engine inlet.