Liquid-fueled supersonic combustion ramjets - A research perspective

Abstract

A review of past and current research applicable to liquid-fueled supersonic combustion ramjets is presented and discussed. An assessment of its strengths and shortcomings is made and, finally, a list of research opportunities that merit consideration in this rapidly expanding area of airbreathing propulsion is presented. Nomenclature = area Cf = average combustor wall skin friction coefficient D = isolator duct diameter d = injector diameter ER = fuel-air equivalence ratio / = fuel-air ratio h - penetration height, enthalpy Ah = driving enthalpy (Ref. 85) M -Mach number P = static pressure q = fuel-to-freestream dynamic pressure ratio, average q = combustor wall heat flux Ree = Reynolds number based on momentum thickness Sd = length of precombustion shock structure in supersonic combustion Ss = total length of precombustion shock structure T = temperature w =fuel jet lateral spreading w =mass flow rate x = axial distance downstream of injection 6 =fuel injection angle 6m = boundary-layer momentum thickness r/c =heat release combustion efficiency f = average combustor skin friction