Report presents an investigation to determine the transonic aerodynamic characteristics of W-plan-form wing of aspect ratio 3.5, taper ratio 0.25, and 60 degree 48 minute panel sweep by using a small reflection plane over which high subsonic and low subsonic Mach numbers are obtained. Comparisons are made between sweptback-wing data to determine the effectiveness of the W-plan modifications.

Report presenting an investigation of the performance of a pair of tubular turbojet combustors interconnected by a 3-inch-inside-diameter ceramic-lined pilot chamber to determine the utility of the pilot chamber for improvement of high-altitude combustion efficiency, lean limits, and minimum engine speed. Results regarding the combustion efficiency and lean-limit blow-out, ignition limits, and altitude operating limits are provided.

Report presenting measurements of the damping in roll of cruciform triangular wings of aspect ratios 0.64, 1.28, and 2.31 at supersonic Mach numbers from 1.5 to 6.0. The models were launched from rifled guns and the time history of the model roll position in free flight was explored. Results regarding the comparison with theory, transonic effects, and comparison with results at other facilities are provided.

Report presenting a comparison of normal load factors measured during combat operations with those measured during an NACA flight program conducted with fully instrumented service airplanes in operational training. Results indicated that for an equal number of maneuvers, normal load factors obtained from the NACA program are greater than those obtained during combat when based on the service-limit load factor.

From Summary: "During a flight investigation of the lateral stability characteristics of a high-speed delta-wing airplane, violent cross-coupled lateral and longitudinal motions were encountered. The maneuver which produced these motions was an abrupt, rudder-fixed aileron roll performed at a Mach number of 0.75 at about 40,000 feet. The motions were characterized by extreme variations in angle of attack and angle of sideslip which caused the airplane to exceed the normal and transverse acceleration limitations."

Report presenting free-falling recoverable model tests conducted at transonic speeds on a model with a triangular wing of aspect ratio 2 and a 45 degree swept tail in the chord plane of the wing. Static- and dynamic-longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at several angles of attack.

Report presenting a preliminary investigation of a variable-area, variable-internal-contraction air inlet at a range of Mach numbers. The total pressure recovery after supersonic compression, total pressure recovery at the exit of the subsonic diffuser, and the pressure distribution along the diffuser walls were measured.

Report presenting a flight investigation on a roll-stabilized ram-jet test vehicle over a range of Mach numbers from 2.3 to 2.7, a range of fuel-air ratio from 0.038 to 0.050, and an altitude range from 3,000 to 40,000 feet. Results regarding test conditions, engine performance, and roll autopilot performance are provided. The engines operated satisfactorily over the test time and the roll-control system operated satisfactorily at the beginning of testing.

An experimental investigation to explore the practicability of a low-speed missile designed to fly with its longitudinal axis pointing along the flight path. The wing and tail surfaces were arranged in a cruciform pattern and the incidence was selected to trim the missile at the desired normal-force coefficient with the body at 0 degrees angle of attack. Results regarding the description of a self-balancing missile and experimental results are provided.

Report presenting testing on 31 airfoils to determine the effects of thickness, trailing-edge bluntness, boattailing, and forward profile on the aerodynamic characteristics of thin airfoils, and to provide a check on available theoretical methods. The airfoils were 2, 4, and 6 percent thick and were tested at two Mach numbers at three Reynolds number in clean condition and one with transition fixed.

Report presenting an investigation at subsonic, transonic, and supersonic speeds of the effect of lip shape on drag, pressure recovery, and mass flow of a nose-inlet air-induction system. Four lips of varying degrees of bluntness were tested on a fuselage model at a range of Mach numbers and angles of attack. Results regarding pressure recovery, net drag, and analysis are provided.

Memorandum presenting an experimental investigation to determine the flutter characteristics of several rectangular wings of variable aspect ratio at a range of Mach numbers. The wings were solid aluminum or steel and were 2, 4, and 6 percent thick. Results regarding the flutter at low and high angles of attack are provided.

Report presenting hydrodynamic planing lifts obtained in a free jet at speeds from 80 to 200 fps for four planing surfaces. The surfaces tested included a flat plate, a longitudinally curved model, a cylinder, and a hydro-ski with a complex-shaped bottom. Lift data was analyzed to show the effect of speed, planing-surface configuration, trim, and wetted-length-beam ratio at high speeds.

Memorandum presenting a determination of the shapes of bodies with minimum pressure drag for a given lift at high supersonic speeds and satisfying conditions of given length and width with the aid of Newton's law of resistance. The resulting shapes have flat bottoms which are also rectangular. To determine if the bodies do actually have improved lift-drag ratios at high supersonic speeds, several wedges satisfying numerically different sets of given conditions were tested at Mach number 5.

Report presenting an experimental investigation to determine the low-speed rolling stability derivatives of a scale model of the Douglas A4D-1. The model was tested in clean and landing configurations with horizontal and vertical tails on and off. The data is presented without analysis.

Characteristics of NACA submerged duct entries and wing leading-edge inlets designed for a 1/4 scale flow model of a fighter-type airplane powered by a jet engine in the fuselage are presented.

Report presenting the performance increase resulting from the addition of fluorine to the oxygen-JP4 rocket propellant combination evaluated experimentally in a 1000-pound-thrust engine with 0, 30, and 70 percent of fluorine by weight in the oxidant. Maximum specific impulse values obtained were 259, 278, and 287 pound-seconds per pound, respectively, at a combustion pressure of 600 pounds per square inch absolute.

Report presenting a study of the acceleration characteristics of a turbojet engine equipped with variable-position inlet guide vanes in the altitude test chamber. Maximum acceleration values for 3 engines of the same model were also obtained during testing and were found to differ as much as 50 percent. Results regarding the effect of fuel step size and inlet guide vane on acceleration, effect of flight condition, reproducibility of engine acceleration, compressor pressure ratio in relation to acceleration, and acceleration with inlet air distortion are provided.

Report presenting an investigation in a mixing-zone apparatus to determine the effects of jet flow on two-dimensional base pressure and the development of supersonic channel flow about a two-dimensional base, with and without splitter plates of different thicknesses. Results regarding the starting cycle for outer streams only, the fully established supersonic flow, and the base pressure between the center jet and outer streams are provided.

Report presenting an investigation at high subsonic speeds to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Testing was conducted at a range of angles of attack, propeller thrust coefficients, Mach numbers, and Reynolds numbers.

Report presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand using the power section of a 5970-pound-thrust, axial-flow turbojet engine. The various portions of the afterburner and procedures used to test it are described. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.

Report presenting an investigation of a model of the Chance Vought XF8U-1 airplane to determine the effect of spin-recovery rockets on the recovery characteristics of the model. The investigation also included tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. Results regarding yaw rockets, thrust-simulation rocket, and roll rockets are provided.

Report presenting preliminary flight-measured chordwise pressure distributions, which have been obtained at a wing midsemispan station of the Douglas X-3 research airplane through a range of angles of attack and Mach numbers. An exploration of the section aerodynamic characteristics is also provided.

Memorandum presenting a force-test investigation to determine whether the static stability characteristics of a twisted and cambered 68.7 degree delta wing could be approximated by a plane wing of similar plan form with dihedral. Results regarding longitudinal characteristics and lateral characteristics are provided.