NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
altitude performance characteristics of tail-pipe burner with variable-area exhaust nozzleAn investigation was conducted in the NACA Lewis altitude wind tunnel to determine effect of altitude and flight Mach number on performance of tail-pipe burner equipped with variable-area exhaust nozzle and installed on full-scale turbojet engine. At a given flight Mach number, with constant exhaust-gas and turbine-outlet temperatures, increasing altitude lowered the tail-pipe combustion efficiency and raised the specific fuel consumption while the augmented thrust ratio remained approximately constant. At a given altitude, increasing flight Mach number raised the combustion efficiency and augmented thrust ratio and lowered the specific fuel consumption.
Document ID
19930086180
Document Type
Other
Authors
Jansen, Emmert T
Thorman, H Carl
Date Acquired
August 16, 2013
Publication Date
August 11, 1950
Report/Patent Number
NACA-RM-E50E29
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
TURBINES, GAS - AFTERBURNING
COOLING - GAS-TURBINE SYSTEMS
ENGINES, TURBOJET

Available Downloads

NameType 19930086180.pdf STI