From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."

Report presenting a compilation of sea-level static and flight-performance data for existing and designed U.S. axial-flow turbojet and ram-jet engines. Factors considered include engine size, performance, and weight, and actual and theoretical performances are compared.

Report presenting a low-speed investigation in the stability tunnel to determine the lateral control characteristics of a 60 degree triangular wing model equipped with half-delta tip controls with areas of 5, 10, and 15 percent of the wing area. Results regarding lateral control effectiveness, rolling effectiveness, and a comparison of control and effectiveness with theory are provided.

Report presenting free-fall tests of a wing-body configuration with a 45 degree sweptback cambered and twisted wing of aspect ratio 6 on a fuselage of fineness ratio 12.4. Results regarding the load and pitching moments and load-coefficient distribution are provided.

Report discussing testing to determine the effect of sweepback on the longitudinal characteristics of a model of the Bell X-5 airplane at Mach number 1.24. Lift, drag, and pitching moments were obtained for several angles of attack. Effects on the drag coefficient and lift-curve slope are described.

"A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered. A particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and therefore is practical for use on supersonic airplanes and missiles. For some Mach numbers the drag coefficient for this type of inlet is larger than the drag coefficient for the type of inlet with supersonic compression entirely inside, but the pressure recovery is larger for all flight conditions" (p. 1).

"An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/19-scale model of the North American T-28C airplane to determine the spin and recovery characteristics. The T-28C airplane is similar to the T-28B airplane except for slight modifications for the arresting hook. The lower rear section of the fuselage was cut out and, consequently, the lower part of the rudder was removed to make a smooth fairing with the fuselage" (p. 1).