SEARCH · Search NASA
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Performance of experimental annular turbojet combustors at simulated high altitude supersonic flight conditions
Effect of fuel injector and liner design on performance of turbojet combustor with vapor fuel
Experimental effect of gas flow transients on heat emission of burning liquid drops in a rocket combustor
Combustor performance using hydrogen fuel at high altitude
Pressure scaling in ramjet combustor with fuel injection
Theoretical models and experimental rocket combustors for study of combustion process instability
Theoretical and experimental models of the study of combustion instability in rocket combustors
Performance characteristics at simulated high altitudes of prevaporizing annular turbojet combustor with low pressure loss
Turbojet combustor and fuel system operation with hydrogen fuel at -400 deg F
Liquid oxygen set behavior during combustion instability in gaseous hydrogen fueled rocket combustor
Design techniques and problems in combustors of turbojet engines operating on boron-containing fuels
Acoustic decay coefficients of simulated rocket combustors
Vaporization analysis of n-heptane in unstable combustor with traveling transverse oscillations using drop-evaporation theory
Drop-size distribution data for ethanol jets atomized by downstream injection into combustion gas stream inside rocket combustor
Thin film, heat flux probe for measuring gas velocities in unstable rocket combustor
Experimental annular turbojet combustor with high velocity air admission through one wall
Supersonic combustor length and contours for optimum performance determined from one- dimensional pressure-area analysis
Experimental discharge coefficients for various types of combustor-liner air-entry holes are presented as a function of a dimensionless flow parameter. In general, scoops and step louvers have higher discharge coefficients and wider flow ranges than flush holes. The effects of size or shape of a given type of hole are small. The proximity of multiple flush holes or the wall inclination of a convergent duct has a negligible effect on discharge coefficient.