Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder

Abstract

Experimental investigation of supersonic flow at Mach number of 2 around a finned ogive cylinder at angles-of-attack ranging from 0° to 16° has been conducted in T-38 trisonic blow-down wind tunnel of the Serbian Military Technical Institute. A short description of testing process and measuring equipment is given. Results of a comparison of experimental and numerical results, that primarily include aerodynamic coefficients and pressure distribution, are presented and discussed. Numerical simulations were performed in ANSYS FLUENT with three Reynolds Averaged Navier-Stokes turbulence models of different complexity. Both structured and unstructured grids were generated, tested and compared and the influence of their nature and size has been considered. Base flow at zero angle-of-attack has been investigated in more detail and the accuracy and applicability of the used models is discussed. Computed fluid flow is presented in the form of pressure coefficient and Mach number contours and velocity vectors.