Scramjet Performance with Nonuniform Flow and Swept Nozzles

Large Eddy Simulation of REST Hypersonic Combustor based on Dynamic Zone Flamelet Model

“…Scramjets with a rectangular-to-elliptical shape-transition (REST) inlet [6][7][8], inlet injection technique [9,10], and an elliptical combustor capable of delivering net thrust at speeds from Ma=7.5 [11], Ma=8 [12], Ma=8.7 [13], Ma=10 [14], and up to 12 [15-17] have been experimentally tested in University of Queensland's T4 Reflected shock tunnel (RST). Numerical studies for uniform-compression and nonuniform-compression scramjets over the flight Mach number range of 7-12 [18]; however, the negative specific impulse was observed for Ma>11. The operating limits are expected to be Ma=15 and 10 for hydrogen and hydrocarbon -fueled scramjets [19].…”

“…Thermally perfect gas behavior was used as described in Eq. (18). The thermodynamic and transport properties of the gas mixture, such as absolute enthalpy, specific heat, thermal conductivity, viscosity, thermal and mass diffusivities are calculated using the open-source chemical kinetics package-II [37] based on the JANAF (Joint Army-Navy-Air Force)-format thermochemical database [38] and a CHEMKINformat transport database.…”