G0500605 Numerical Analyses of flow field with crossflow-induced transition

Abstract

Boundary layer transition is one of the most important phenomena to reduce aerodynamic drag. In JAXA, aFJR project has started from 2013. In this project, it is one of the important research task that expanding laminar boundary layer region on fan rotor blades surface to improve aerodynamic efficiency of fans. To realize that, prediction of boundary layer transition by CFD is important. Flow angle in boundary layer on rotor blades surface is sometime different from that of main flow (outside of boundary layer). This situation, called as crossflow, induces boundary layer transition. The transition induced by crossflow is important to design high aerodynamic efficiency fan rotor blades. We develop a turbulence model to predict transition induced by crossflow. In this paper, we adopted three shapes of nose cone for Supersonic Transport (SST) to verify our turbulence model. Numerical results have been compared with those in experiments. From the results, it was confirmed that the prediction accuracy of our turbulent model depends on the nose cone shape.