Abstract
The work concerns plane flows around wing sections at high free stream Mach numbers, limited by the validity of the assumptions that specific heats and Prandtl number are constant. The results of the evaluation by means of a commercial CFD code of simple predictive methods for skin friction, recovery temperature and heat flux at the wall with compressible boundary layer are presented for two wing section shapes, typical for supersonic flows: a rhomboidal shape with all laminar and all turbulent boundary layer flow conditions, with four thermal boundary conditions at free stream Mach number 1.5 and 2; a lenticular shape with laminar boundary layer flow and adiabatic wall conditions, at free stream Mach number 2. The results of this evaluation seem to contain interesting indications to evaluate CFD capability and to develop new investigations concerning predictive methods.
Authors: M. Maganzi, L. Polito
Conference/Journal: AIDAA XXIV International Conference, 18-22 September 2017, Palermo – Enna (Italy)
Keywords: boundary-layer, supersonic flow, predictive methods, CFD
