Altitude-wind-tunnel Investigation of J47 Turbojet-engine Performance

Abstract

An investigation has been conducted in the NACA Lewis altitude wind tunnel to evaluate the performance of the J47 turbojet engine over a range of simulated altitudes from 5000 to 50,000 feet, simulated flight Mach numbers from 0.21 to 0.97, and a complete range of engine speeds. Data are presented to show the effects of altitude at a flight Mach number of 0.21 and of flight Mach number at an altitude of 25,000 feet. The performance data are generalized by two methods to determine the range of flight conditions for which engine performance may be predicted from performance data obtained at a given flight condition