Report presenting an investigation of an NACA 1-80-100 nose inlet fitted alternately with an elliptical, a parabolic, a 14 degree-inch conical, and a 22 degree-inch conical central body at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements were obtained at 0 degrees angle of attack through a range of Mach numbers. Results regarding tunnel boundary interference, surface-pressure distribution, external drag, pressure recovery, and propulsive thrust comparison are provided.

"Theoretical pressure distributions on nonlifting circular-arc airfoils in two-dimensional flows with high subsonic free-stream velocity are found by determining approximate solutions, through an iteration process, of an integral equation for transonic flow proposed by Oswatitsch. The integral equation stems directly from the small-disturbance theory for transonic flow. This method of analysis possesses the advantage of remaining in the physical, rather than the hodograph, variable and can be applied in airfoils having curved surfaces" (p. 1).

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.

Memorandum presenting techniques for the measurement of the energy spectrum of flow fluctuations in both axial and lateral flow directions. A simple spectrum analysis is presented by which quantitative distinction may be made between turbulence and the flow disturbances associated with sound waves in ducts. Results regarding the measurement and analysis of turbulent-flow fields containing random and periodic flow fluctuations, effect of random sound disturbances on turbulence spectrum, and effect of combustion on combustor approach-stream spectrum are provided.

Memorandum presenting an investigation of the starting characteristics of mixed oxides of nitrogen - liquid ammonia rocket engines with light metal additives in the ammonia flow line for ignition. The oxidant consisted of 70 percent by weight nitrogen tetroxide and 30 percent nitric oxide. Results regarding the ignition experiments with 100-pound-thrust engine, 1000-pound-thrust engine experiments, and low-temperature experiments are provided.

Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade air- and liquid-cooling systems for turbojet application in guided missiles and supersonic interceptor aircraft. Results regarding the coolant passage heat-transfer-coefficients, nonrefrigerated air-cooling-system characteristics, and refrigerated-air-cooling-system characteristics are provided.

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)."

Memorandum presenting an analytical evaluation of the air and fuel specific-impulse characteristics of magnesium, magnesium-octene-1 slurries, aluminum, aluminum-octene-1 slurries, boron, boron-octene-1 slurries, carbon, hydrogen, methylnaphthalene, diborane, and pentaborane. Adiabatic constant-pressure combustion temperature, air specific impulse, fuel specific impulse, and equilibrium composition data are given for each fuel over a range of equivalence ratios.

Report presenting flight tests conducted on two different inlet configurations, a submerged divergent-wall inlet and scoop inlet, to determine their characteristics when installed on a YF-93 airplane. Measurements were made of the pressure-recovery characteristics of the inlets and overall airplane drag for each configuration. Results regarding the induction-system efficiency, airplane drag, and a relative comparison of the inlet installations are provided.

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 presenting a method for calculating the aerodynamic forces on the blades of a dual-rotating propeller with its thrust axis inclined to the air stream. Comparison of the fluctuating aerodynamic forces due to pitched or yawed operation of a dual-rotating propeller show that the fluctuation in forces on the front component tend to be greater than those on the rear component.

Report presenting an investigation to determine the effects on lift, drag, and pitching moment of a reduction of the thickness ratio of a triangular wing at a range of Mach numbers and Reynolds numbers. Removing the outer 24.9 percent of the span of a wing was also explored.

Report presenting techniques for the measurement of the energy spectrum of flow fluctuations in both axial and lateral flow directions. Data indicated that the energy spectrum of the turbulence is not affected by periodic and random sound disturbances outside the frequency containing the disturbances.

Report presenting an approximate, quasi-three-dimensional design procedure adapted to the design of high solidity, impulse-type supersonic compressors. The method is applied to a compressor rotor with a tip speed of 1600 feet per second in air, an inlet hub-tip radius ratio of 0.75, and an axial discharge relative to the rotor. Results regarding the overall performance, rotor-entrance conditions, static-pressure profiles, discharge conditions, and discharge surveys are provided.

Report presenting studies of some of the effects of parameters such as Mach number, blade angle, and structural damping on the flutter of model helicopter rotor blades in the hovering condition. Forward movement of the blade chordwise center-of-gravity location tended to raise the flutter speeds at low pitch angles, but had no effect at high pitch angles. The significant flutter data for the tests along with detailed descriptions of the models are included to facilitate more detailed analyses.

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.

Report presenting an investigation of the low-speed stability and control characteristics of a modified scale model of the MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. The modifications of the design included an increase in slotted-flap span, a redesigned tip aileron, fuselage tail cone, and speed brakes.

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.