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Present experience with aircraft gas turbine lubricants is discussed in detail and current “problem areas” pin-pointed. A discussion of possible future turbine lubricating systems and lubricants is given. Although present lubricants are doing a satisfactory job in current aircraft, greatly improved lubricants will be required for future gas turbines.

Some of the problems associated with the installation and use of a thrust reverser are best studied by means of full-scale tests. This paper describes two full-scale thrust-reverser installations tested by the NACA, one in a pylon-mounted engine simulating that on a jet bomber or transport and the other in a fighter-type airplane. The effects of reverse thrust on the airplane and engine are emphasized.

This report will present the latest information on the state of the art of jet thrust reversers as it exists in the United States. During the past two years small and full scale testing and also prototype testing has been conducted. Full scale and prototype units have been statically tested on non-afterburning and afterburning engines. Reverser performance has been measured throughout the engine operating range and included full reverse thrust, modulated thrust and some directional control information. Data is now available which shows reverse thrusts of approximately 40 to 80 percent are possible with little or no effect on over-all aircraft and engine performance.

The general problem of applying propulsion systems to supersonic aircraft is discussed briefly and it is shown that neither turbojets nor ramjets are entirely satisfactory when used by themselves. A satisfactory solution does result when the powerplants are combined; high supersonic performance then can be achieved without sacrifice of subsonic capability. In order to avoid the confusion resulting from the comparison of propulsion system performance using the special parameters associated with each type of engine, performance is compared along operating altitude-Mach number paths in terms of thrust and specific fuel consumption only. The combined propulsion system arrived at offers promise of good performance, light weight, low cost, and simple installation. The realization of these goals depends on an aggressive research and development program.