Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.

Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.

Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.

Report presenting an investigation to determine the effect of several seeker-nose configurations on the static longitudinal stability, canard control characteristics, and lift and drag at Mach number 1.60 of a canard-type ramjet missile with 70 degree delta canard control surfaces and 70 degree delta wings. The tests indicate that, for the most part, the configurations tested exhibited no significant difference in static longitudinal stability or horizontal-canard control effectiveness.

"In the present paper attention is directed to the aerodynamic parameters, the so-called stability derivatives, that affect the lateral behavior of airplanes and missiles. The discussion is centered on three important quantities, the effective-dihedral derivative, the directional-stability derivative, and the damping-in-roll derivative. These quantities are considered for a large angle-of-attack range at subsonic speeds" (p. 1).

An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane performance. These parameters included compressor pressure ratio, compressor efficiency, turbine-inlet temperature, afterburner temperature, engine specific weight, and air-handling capacity. The effects of using a convergent-divergent exhaust nozzle and of changing the design flight Mach number were also investigated.

Memorandum presenting minimum spark-ignition energies for 12 pure fuels measured at reduced pressure, and the data obtained were extrapolated to 1 atmosphere. Some of the fuels investigated included normal and cycloparaffins, olefins, carbon disulfide, and oxygenated compounds such as alcohol, ether, propylene oxide, and tetrahydropyran.

Memorandum presenting a wind-tunnel investigation at low speed to determine the path and motion of a scale model of the Douglas XF4D-1 escape capsule without the drogue parachute when jettisoned by jet ejection. The investigation included determination of the vertical and horizontal accelerations of the capsule. Results regarding the ejection at zero airspeed, ejection at 570 feet per second, and at 863 feet per second are provided.

From Introduction: "Because of variation in the static-pressure drop across the porous material and in the cooling air required along the length of afterburner combustion chambers, a prescribed distribution of permeability is usually necessary. However, as a preliminary investigation, this report is concerned only with the attainment of uniform permeability. The results of an experimental investigation, conducted at the NACA Lewis laboratory, to determine the permeabilities of five thick meshes of wire filter cloth are presented herein."

Report presenting an experimental investigation in the 8- by 6-foot supersonic wind tunnel to determine the performance characteristics of a twin-duct side intake system joining into a common duct and utilizing two-dimensional 6 degree compression ramps mounted on a supersonic airplane at Mach numbers 1.5 and 1.7.

Report presenting an investigation in an altitude test chamber to determine criteria for the design of flame holders for a turbojet-engine afterburner. The performance of ten flame holders was obtained in a louvered-liner afterburner operated at constant afterburner-inlet temperature over a range of fuel air ratio and total pressures. Results regarding the effect of gutter cross-sectional shape, effect of gutter width, effect of flame-holder blocked area, effect of trailing and interconnecting gutters, and effect of altitude on V-gutter flame holders are provided.

Report presenting an investigation of the performance of a 20-inch-diameter ramjet engine with a high-heat-release pilot burner conducted at zero angle of attack in a free-jet test facility at a Mach number of 3.0. Two flame-holder configurations were used in conjunction with the high-heat-release pilot burner over a range of altitudes. Results regarding the performance of the high-heat-release pilot burner and performance of combustion-chamber configurations are provided.

Report presenting a comparison of fixed-geometry, translating-spike, and bypass-inlets on the basis of turbojet- and ramjet-engine performance. Results regarding a comparison of the experimental data and its application to ramjet and turbojet engines are provided.

"Theoretical calculations of the stability derivatives at supersonic speeds for a high-speed airplane configuration are presented. The range of Mach numbers considered includes those cases for which the wing and tail surfaces have subsonic leading edges, supersonic leading edges, and combinations of the two. The methods of analysis are discussed; these represent detailed consideration of the important effects and contributions of the various airplane components utilizing available theories and theoretically justifiable and reasonable approximations" (p. 1).

From Introduction: "An investigation of the variation in turbine-entrance equivalent weight flow for a two-stage turbine equipped with an adjustable turbine stator is presented in reference 1. A general analytical investigation of turbine stator adjustment is presented in reference 2. In reference 2, the effect of stator adjustment on turbine off-design performance is also investigated by analytically computing the performance of a particular single-stage turbine."

From Summary: "A ceramic consisting nominally of 75 percent molybdenum disilicide and 25 percent alumium oxide was investigated to determine its thermal shock characteristics and high-temperature strength properties. In a rim-quench thermal shock evaluation, the material was found to be superior to pure molybdenum disilicide. In a simulated altitude blow-out test, the material withstood an average of 2.5 cycles when quenched from 1800 degrees Fahrenheit."

Memorandum presenting a screening of various hydroxides for use in nuclear reactors as possible coolant moderators for operation at temperatures of about 1500 degrees Fahrenheit. The hydroxides that appear stable at a pressure of about 1 atmosphere are those of sodium, potassium, rubidium, lithium, barium, and strontium. Results regarding the core uranium investments and reflector savings are provided.

Report presenting an extension of NACA RM A52C14 about inlet design and performance for Mach numbers of 1.5 to 2.0. A two-dimensional inviscid analysis is used to compare the performance of several types of inlets when used in conjunction with a turbojet engine with constant-volume air flow. Results regarding air delivery and air requirements, drag factors, evaluation of inlet performance, significance of the drag summation, and inlet and engine-matching considerations are provided.

A study of the effects of variations in lateral-oscillatory characteristics on air-to-air tracking performance has been made, using a conventional, propeller-driven fighter airplane equipped with servo devices for varying these characteristics in flight. Tracking runs were made both in smooth air and in simulated rough air. The lateral-oscillation period, damping, and roll coupling were varied over wide ranges during the investigation.

From Introduction: "This report presents the initial study, the tracking performance of typical fighter airplanes with fixed gunsights. The types of airplanes tested afford two comparisons of particular interest: that between typical World War II and currently operational fighters of greatly increased speed and altitude, and that between conventional and irreversabile power-boosted controls with artificial feel, both installed on the same airframe."

Report presenting engine evaluation tests of twelve sets of cermet turbine blades. The first five runs were similar to previous engine tests, but the remaining ones were modified based on information gained during the first runs.

Memorandum presenting testing conducted to determine the conductivity of magnesium oxide, stainless steel, and uranium oxide powders in various gases at a range of temperatures. Results regarding the experimental effective conductivities, comparison of analytical and experimental results, and effect of pressure on conductivity are provided.

Report presenting an investigation of the thrust loading by wake surveys in the slipstream of a full-scale supersonic-type three-blade propeller (the Curtiss-Wright 109622) that was conducted in the transonic tunnel. Integrated-thrust coefficient values were found to be in good agreement with the force data. Results regarding thrust loading at constant advance ratios, at advance ratios for maximum efficiency, and lift-coefficient distribution are also provided.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a body-control arrangement at Mach number 1.61. A 70 degree delta canard-type control mounted in the horizontal plane and with a span-to-body-diameter ratio at the control trailing edge of 2.52 tested both fixed and moving in the presence of a long cylindrical body with a parabolic nose.