Memorandum presenting results of a free-flight investigation over a range of Mach and Reynolds numbers to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. The missile has a wing, body, and vertical tail, but has no horizontal tail. Results regarding basic data, drag, trim, lift and static stability, damping, and static pressure are provided.

Report presenting an investigation of 47 experimental tubular designs embodying variable primary-air openings to control the fuel-air ratio in the combustion zone at simulated high-altitude operating conditions for a representative 5.2-pressure-ratio engine. The performance characteristics considered were combustion efficiency, operating range, and pressure loss. Results regarding the effect of fuel injector design, effect of primary-air baffles, and performance characteristics of the best models are provided.

Report presenting an investigation on a 30 degree sweptback wing-fuselage model in the 300 mph 7- by 10-foot tunnel to determine the effect of flap-type spoilers and spoiler-slot-deflectors on the chordwise and spanwise pressure distributions over the wing and controls. The results regarding the tabulated pressure, section force, and moment coefficients for six spanwise stations and curves of the variation of the total integrated force and moment coefficients with angle of attack for various control projections are provided.

From tests on cylindrical target-type thrust reversers, it was found that the reverser frontal area, lip angle, end-plate angle, and end-plate depth had important effects on reverse-thrust performance. Frontal area, reverser depth, lip angle, and end-plate angele had important effects on the spacing required for unrestricted nozzle flow. For reverse-thrust ratios greater than 64 percent, the reversed flow attached to the 7 degree cowl in quiescent air. Swept-type cylindrical reversers were generally unstable. The thrust-modulation characteristics of a cylindrical target-type thrust reverser were found to be satisfactory.

Report presenting a wind-tunnel investigation at low speed to determine the effects of sideslip on the static longitudinal trim characteristics of three fighter-type airplane models. The three models consisted of a 45 degree swept-wing model with a horizontal tail geometrically similar to the wing and mounted slightly below the wing, a clipped-delta-wing model with a horizontal tail mounted in a moderately high position, and a 60 degree delta-wing with no horizontal tail. Results regarding static longitudinal stability, variation of pitching-moment coefficient with sideslip, effect of modifications to Model B on static longitudinal stability and variation of pitching-moment coefficient with sideslip, and static lateral stability are presented.

Memorandum presenting a flight investigation of the Bell X-5 variable-sweep research airplane in the 45 degree wing sweptback configuration over a range of Mach numbers. Lift and drag values are presented and a comparison is made with data obtained with a wing sweepback of 59 degrees.

Report presenting an investigation in an NACA free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths and three fuel-distribution systems were investigated over a range of fuel-air ratios and at two air flows. Results regarding the combustor performance and ignition data, velocity profile, and starting characteristics are provided.

Report presenting an investigation made in the 7- by 10-foot tunnel of the static lateral and directional stability and some tail-load characteristics of a model with a highly tapered swept wing and two horizontal-tail positions. Testing were made with the horizontal tail located at the tip of the swept vertical tail and with the horizontal tail located in the wing-chord plane extended. Results regarding static lateral and directional stability and vertical-tail loads are provided.

Memorandum presenting a turbojet engine with a centrifugal-flow compressor which permitted overspeed, overtemperature operation and was modified for spray cooling. The effectiveness of spray cooling as a method which permits operation at overspeed, overtemperature conditions with this engine was investigated and the overspeed, overtemperature performance was obtained. Results regarding the cooling system performance, turbine performance, and engine performance are provided.

Report presenting an experimental investigation conducted in the supersonic wind tunnel at three Mach numbers on a translating-spike inlet analytically designed to keep the cone shoulder downstream of the cowl-lip station without a net internal contraction. The inlet in this investigation had an internal cowl-lip angle of 17.5 degrees and was constructed to have the same inlet capture area and maximum cross-sectional area as a previously tested inlet with an internal cowl-lip angle of only 7 degrees. Results regarding the total pressure recovery, effect of spike translation, external drag coefficients, and effective thrust parameter are provided.

From Introduction: "The primary purpose of the wing instrumentation was to obtain data for use in design of NACA research missiles; however, it is believed that the wing is representative of typical supersonic designs and that the data will be of general use and interest. Only the wing data are reported herein."

From Summary: "An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry."

Report presenting vibratory stress measurements on a supersonic-type propeller for forward Mach number up to 0.95. Results regarding the bending stress and torsion stress are provided.

From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."

Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. The purpose behind the investigation was to investigate the idea that luminous radiation from nongaseous substances in the afterburner gas stream might be present and vary significantly with pressure.

Report presenting a 45 degree sweptback wing of aspect ratio 3, with twist and a distributed type of camber, tested in combination with a body of fineness ratio 12.5 to determine the lift, drag, and pitching-moment characteristics.

Memorandum presenting net jet thrusts for stoichiometric hydrocarbon-air, hydrogen-air and pentaborane-air mixtures for equilibrium and frozen expansion in the exhaust nozzle at flight Mach numbers up to 10. Examinations of the dissociation products involved and the energies associated with them, for the hydrocarbon- and hydrogen-air mixtures indicated that a major portion of the dissociation energy for the hydrocarbon mixture is involved in the carbon monoxide molecule.

Report presenting performance estimates for a family of airplanes designed to cruise at Mach number 4.25 and using General Electric AC-210 ramjet engines. The airplane was designed to carry a payload of 10,000 pounds and use a crew of one. Results regarding the shield weight, engine weight, number of engines, and nozzle-velocity coefficient are provided.

Report presenting an investigation of an axial-flow compressor rotor with an inlet hub-tip radius ratio of basically zero. Results regarding the radial distribution of total-pressure ratio and efficiency, measured pressure ratio at design speed, weight flow, and low-speed cascade data are provided.

Report presenting an investigation in the 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics of a 1/28-scale dynamic model of the North American FJ-4 airplane. Results indicated that either a flat-type or a steep-type spin maybe obtained when the airplane is spinning erect. Results regarding inverted spins, loading condition, spin-recovery rocket tests, and spin-recovery parachute tests are provided.

Report presenting seven injectors of four different types tested for use with JP-4-oxygen-fluorine propellant combinations. High characteristics velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding the injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.

Report presenting an investigation of the static lateral stability characteristics of a swept-wing fighter-type airplane with three vertical-tail configurations and two wing configurations at an altitude of 40,000 feet over a range of Mach numbers. Data was obtained in several conditions, including constant-heading sideslips and wings-level turns, aileron rolls, and abrupt rudder pulses. Results regarding the sideslip characteristics, lateral control, and control effectiveness derivatives are provided.

From Summary: "The manner in which imperfect space stabilization of the tracking radar influences the flight path stability of an automatic interceptor during the attack phase is illustrated by means of flight and analog-computer time histories. It is shown analytically that these effects may be interpreted in terms of a destabilizing airplane rate feedback which can be canceled by an additional compensatory feedback in the radar tracking loop."

Memorandum presenting surveys of the impact pressure of the flow to obtain information for determining pressure losses in four different turbosupercharger nozzle boxes. The data indicated substantial differences in total head loss among the boxes and the existence of sharply defined high-loss regions in portions of the nozzle annulus.