Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowable center-of-gravity travel are provided.

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 the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.

The results of flow tests on a drawbar for the General Electric reactor segment test in the MTR are reported. The drawbar is a T-shaped obstruction located as close to the upstream face of the reactor test segment as possible without serious flow distortion ; the drawbar is required for instrumentation leads and segment insertion and removal in the MTR. The effect of drawbar upstream distance on velocity distribution across the segment face is evaluated for several Reynolds numbers.

Memorandum presenting an investigation conducted in the icing research tunnel to determine the icing characteristics, the effects of icing on radar operation, and the protection requirements for two radome configurations. The radomes were for the F-89 airplane and were investigated at airspeeds up to 290 miles per hour, air total temperatures from -15 to 20 degrees Fahrenheit, water contents up to 1.0 gram per cubic meter, and angles of attack of 0 and 4 degrees.

From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented."

Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.

Memorandum presenting steady-state and transient characteristics of the J34-WE-32 turbojet engine with electronic power regulator as obtained in the altitude wind tunnel to determine the effects of engine and control limits on the performance. Limits on the fuel valve and exhaust nozzle area influence any schedule of speed and temperature. Results regarding the effect of limits on operating schedule, effect of altitude on safe operating range, effect of minimum fuel flow settings on transient performance, and some potential problems are provided.

From Summary: "The literature pertaining to the preparation, physical properties, corrosiveness, thermal stability, constitution, and analysis of various nitric acids is reviewed primarily with respect to their use as rocket oxidants. Conflicting data are evaluated and recommendations for additional experimental work are indicated. Reactions of nitric acid which could occur during the starting and steady-stage phases of rocket operation are discussed and probable mechanisms are selected on the basis of reported thermal and kinetic data."

Report presenting an investigation to determine the effect of turbulence generated by different sizes of wire grid on the minimum spark-ignition energy of a flowing propane-air mixture. Gas-stream velocity, size of turbulence promoter, and distance from the promoter plate to the electrodes on minimum ignition energy were evaluated and the effects are shown in figures.

Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a thin delta wing equipped with various arrangements of double slotted, single slotted, plain, and split flaps. The wing was a flat plate with beveled leading and trailing edges and had a maximum thickness ratio of 0.045, and 60 degrees sweepback of the leading edge.

Report presenting pressure fluctuations measured near the trailing edge of the wing and near the leading edge of the tail of a scale model of the X-1 airplane with a 10-percent-thick wing in the 16-foot transonic tunnel. Results regarding frequency analyses are also provided.

Report presenting an experimental investigation to determine some of the characteristics of an inset tab as an aerodynamic balance in the Mach number range between 0.7 and 1.4 using a zero-lift rocket-propelled model in free flight. Results regarding the variation of the aileron floating angle, the wing-tip helix, the balancing effect, and the penalty occurred throughout the Mach number range are provided.

Report investigation Freon-12 as the working fluid for a 14-inch-diameter supersonic mixed-flow axial-discharge rotor of the impulse type. The whole series of tests was performed twice, once with guide vanes that underturned the air and gave a lower relative inlet velocity and once with a set that gave the design values for velocity and direction. Results regarding the overall performance characteristics, entrance flow, internal pressure patterns, exit flow, and rotor losses are provided.

Investigation of the internal performance characteristics of several jet-exit configurations over a wide range of pressure ratios, which are summarized to provide an overall picture of jet-exit performance. The configurations investigated include a convergent nozzle, fixed convergent-divergent nozzles, an adjustable plug-type convergent-divergent nozzle, and jet ejectors. Results regarding the performance of several jet-exit configurations and matching adjustable jet exits to supersonic aircraft 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."

Report presenting an investigation at transonic speeds using the wing-flow method to determine the longitudinal-control effectiveness and downwash characteristics of a 1/30-scale semispan model of the Bell X-5 airplane with three different degrees of sweepback. Lift, drag, and pitching moment are presented for various angles of attack for several horizontal-tail settings and with the tail off for each angle of sweep tested.

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 longitudinal-damping data in the form of the pitching-moment derivatives and summarized from flight tests of rocket-propelled models and full-scale airplanes. 22 models and 4 airplanes are examined in the study and the damping derivative results are generalized.

Report presenting an investigation of the hypersonic similarity law for steady flow about bodies of revolution by correlating the forces and moments from tests at a range of Mach numbers and angles of attack. The data for the lifting cones and ogives are correlated by the hypersonic similarity law. Results regarding the similitude for lift and pitching moment and similitude for drag are provided.

Report presenting testing of three scale models and a full-scale configuration of systems for ducting cooling air through a turbojet engine tail cone to a cooled turbine rotor in order to determine pressure-loss characteristics.

Memorandum presenting an investigation of the use of a small quantity of fluid that ignites spontaneously within nitric acid to initiate the acid-gasoline reaction carried out in a 200-pound-thrust uncooled engine with a characteristic length of 30 inches at a range of temperatures. The starting process was divided into two phases: ignition and transition. Results regarding ignition temperature limits, effect of temperature on allowable igniter fuel flow, optimum valve opening time for ignition, effect of temperature on transition process, effect of running-fuel reactivity on transition, and tar-forming tendencies of igniter fuels are provided.

Report presenting an investigation to determine the predictability of using ceramals with comparatively low strategic material content for the blades of aircraft turbines, including testing with four different blade root configurations. The most favorable results were obtained for ceramal turbine blades with single serration interlock and dovetail root configurations. Results are also provided for fir-tree blade runs and 4-pin blade runs.

Report presenting an investigation to determine the effect of leading-edge chord-extensions on high-lift pitching moment and performance characteristics at subsonic and transonic speeds. Three models with the same wings were used. Results regarding low-speed development and high-speed characteristics are provided.