Numerical and experimental assessment of transonic turbulent flow around ONERA M4 model

Abstract

Experimental investigation of transonic flow at Mach number of 0.84 around a subsonic/transonic transport calibration model ONERA M4 at four different angles-of-attack has been conducted in T-38 trisonic blow-down wind tunnel of the Serbian Military Technical Institute. Experimental results include relative pressure and pressure coefficient distributions along three wing sections. Obtained aerodynamic performance data present a good basis for CFD studies. Both experimental and numerical set-ups and processes are briefly described. Numerical simulations are performed in ANSYS FLUENT 16.2 with several different turbulence models employed. Two different sets of results are presented and compared. Pressure distribution along the wing surface, sonic bubble on the wing suction side and wingtip vortex have been investigated in more detail and presented in form of contours and iso-surfaces.