Laminar Design for Supersonic Civil Transport

Abstract

The paper presents a design methodology for supersonic wing sections with hybrid laminar flow control. The approach is based on coupled Euler/boundary layer flow simulation and linear stability analysis for transition prediction. The investigations show that combinations of simple pressure distribution shapes can be used to optimize airfoils for maximum extent of laminar flow and hence minimum friction drag. NOMENCLATURE α = angle of attack c f = skin friction coefficient c l = lift coefficient c p = pressure coefficient c q = suction coefficient; c q =(V s ρ) w Ma = Mach number Re = Reynolds number based on freestream condition Φ LE = Leading edge angle N tr = Transition N-factor (envelope method)