Propellants and combustion / American Institute of Aeronautics and Astronautics ; Volume 2 of 2
Propellants and combustion / American Institute of Aeronautics and Astronautics ; Volume 1 of 2
NUMERICAL STUDY ON COMBUSTION CHARACTERISTIC OF MICRON ALUMINUM PARTICLE
FLAME SPEED OF TURBULENT PREMIXED KERNEL IN TURBULENT FLOWS
DEVELOPMENT AND TESTING OF PULSE GUNS FOR COMBUSTION INSTABILITY TESTING
BROADBAND, MID-INFRARED LASER-ABSORPTION MEASUREMENTS OF TEMPERATURE, CH4, AND C3H8 IN FLAMES
UNCERTAINTY QUANTIFICATION ANALYSIS OF RANS OF SPRAY JETS
CHARACTERIZATION OF THE MELT LAYER OF AMMONIUM PERCHLORATE SINGLE
EFFECT OF FUEL TEMPERATURE ON EMISSIONS AND STRUCTURE OF A SWIRLSTABILIZED FLAME
DESIGN AND CHARACTERIZATION OF THE DUAL INDEPENDENT SWIRL COMBUSTOR FACILITY (DISCO)
IMPROVED CHEMICAL KINETIC MODEL REDUCTION IN PYMARS FOR LIQUID PROPELLANTS
MEASUREMENT OF RAYLEIGH-BRILLOUIN SPECTRAL LINESHAPES OF COMBUSTION-RELEVANT GASES AT HIGH PRESSURE
IGNITION OF JET FUEL ASSISTED BY A HOT SURFACE AT AIRCRAFT COMPRESSION IGNITION ENGINE CONDITIONS
HIGH-SPEED VIDEO ANALYSIS OF LUBRICATING OILS UNDERGOING HOT-SURFACE IGNITION
MEASUREMENTS OF THE VAPOR PRESSURE OF LIQUID HYDRAZINE ABOVE ITS NORMAL BOILING POINT
DETERMINATION OF NITRIC OXIDE CONCENTRATIONS IN MIXTURES WITH NITROGEN TETROXIDE VIA IR SPECTROMETRY
INVESTIGATION OF COMBUSTION INSTABILITIES IN A FULL FLOW STAGED COMBUSTION MODEL ROCKET COMBUSTOR
STUDIES ON FLAME SPREAD ACCELERATION, DETONATION KERNEL IN A DUAL-THRUST ROCKET
PILOT INJECTOR REDESIGN TO REDUCE N+3 CYCLE EMISSIONS FOR A GAS-TURBINE COMBUSTOR
FLOW FIELD CHARACTERIZATION OF A THIRD GENERATION SWIRL-VENTURI LEAN DIRECT INJECTOR