The high-work-output turbine had an experimental efficiency of 0.830 at the design point and a maximum efficiency of 0.857. The downstream stator was effective in providing axial flow out of the turbine for almost the whole range of turbine operation.

Report presenting limited flight-test data obtained from an automatically controlled interceptor during runs in which oscillatory rolling motions occurred that were then compared to the pilot's comments about his ability to tolerate the imposed lateral oscillations. The alleviation of the undesirable effects of oscillatory lateral accelerations and their effects on piloting task were also considered. The marginally tolerable limit of acceleration forces on the pilot's head was found to be about 0.4 to 0.5g.

Report presenting theoretical rocket performance for frozen and equilibrium composition during expansion for the propellant combination of liquid hydrogen and liquid fluorine at a chamber pressure of 600 pounds per square inch absolute and several pressure ratios and oxidant-fuel ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity.

Report presenting a theoretical investigation of the attack phase of an automatically controlled interceptor. Three types of control systems were simulated on an analog computer: a modern high-speed interceptor, a dynamically perfect radar-controlled director-type guidance system for a lead-collision course, and a velocity-type automatic pilot. The primary flight maneuver tested was a 5g climbing turn with roll and acceleration commands applied simultaneously.