Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.

From Summary: "An experimental technique has been developed which enables a determination of the net propulsive force acting on an afterburner-equipped airplane in flight. The thrust measurement is based on the variation of static and total pressure and stagnation temperature across the fuselage exit as determined by a swinging pitot-static pressure and temperature probe. The details are also presented for an air-cooled fixed-pressure probe for the determination of basic engine thrust."

From Summary: "With low-freezing red fuming nitric acid in a modified open-cup apparatus, ignition delays were determined in the temperature range -40 degrees to -105 degrees Fahrenheit for allylamine, disallylamine, mixed alkyl thiophosphites, ethylenimine, blends of each of these fuels with triethylamine, and blends of ehtylenimine with n-heptane. The data indicate that allylamine, mixed alkyl thiophosphites, and ehtylenimine can be blended with as much as 70 percent triethylamine and still ignite with average delays less than 30 milliseconds at -40 degrees Fahrenheit, and approximately 40 milliseconds at -76 degrees Fahrenheit (-60 degrees Celsius)."

Report presenting an investigation in the supersonic wind tunnel on an inlet employing conical flow separation from a probe extending upstream from a hemispherical-nosed centerbody. Pressure-recovery and drag characteristics for the inlet were very nearly comparable with a conical-spike inlet, but compared less favorably at Mach numbers below 2.0. A large reduction in pressure recovery and mass flow was obtained at angle of attack.

Report describes the development of the Langley annular transonic tunnel, a facility in which test Mach numbers from 0.6 to slightly over 1.0 are achieved by rotating the test model in an annular passage between two concentric cylinders. Data obtained for two-dimensional airfoil models in the Langley annular transonic tunnel at subsonic and sonic speeds are shown to be in reasonable agreement with experimental data from other sources and with theory when comparisons are made for nonlifting conditions or for equal normal-force coefficients rather than for equal angles of attack. The trends of pressure distributions obtained from measurements in the Langley annular transonic tunnel are consistent with distributions calculated for Prandtl-Meyer flow.

Memorandum presenting a comparison of the maximum speed of response that can be attained by three missile configurations, a variable-incidence-wing, a canard, and a tail-control, in combination with a particular proportional navigation guidance system. The configuration that allows the most rapid overall guidance-system response depends on the control-system characteristics. Results regarding the rate-only feedback and rate and normal acceleration feedback are provided.