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."

"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).

Report discussing free-flight tests of normal-shock nose-inlet models with 1-series, parabolic, and conic cowling profiles in order to investigate the external drag characteristics at an angle of attack of 0 degrees. The testing occurred at a variety of Mach numbers, mass-flow ratios, and Reynolds numbers. Information about the effect of afterbody length, basic data, and effect of cowl shape is provided.

"An investigation was made to determine the static longitudinal and lateral stability and control characteristics of a 1/6-scale model of the revised Republic XF-84H airplane with and without the propeller operating. The model had a 40 degree swept wing of aspect ratio 3.45 and was equipped with a thin, three-blade supersonic-type propeller. Modifications incorporated in the revised model included a raised horizontal tail, increased rudder size, wing fences at 65 percent semispan, and a modified wing leading edge outboard of the fences" (p. 1).

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of body contouring as specified by the transonic drag-rise area rule on the aerodynamic characteristics of a delta wing-body combination at Mach numbers of 1.41 and 2.01. Body contouring reduced zero-lift drag of a delta wing-body combination from that of a basic wing-body combination without contouring by 18 percent at Mach number 1.41 and 6 percent at Mach number 2.01. Results regarding the characteristics at zero lift and characteristics for the lifting condition are provided.

Memorandum presenting an investigation of modifications to an indented body which was originally designed on the basis of the transonic drag-rise rule to determine the effects on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination. The investigation covered a range of Mach numbers and angles of attack. Results regarding lift, drag for the nonlifting case, drag for the lifting case, maximum lift-to-drag ratios, and pitching moment are provided.

Report presenting results of a systematic study in the 8- by 6-foot supersonic wind tunnel to determine the effect that area distribution in the subsonic diffuser might have on stability and overall performance of conical-type supersonic diffusers. Drag, pressure recovery, and mass flow are presented for five diffusers designed for maximum mass flow at Mach number 2.0.

Report presenting a series of turbine wheel designs made for a turbojet engine with an axial-flow compressor. The designs were made to determine the influence of air-cooling on overall engine design, weight, critical-material content, and complexity and to assist with construction of research model full-scale turbines.

"Eighty pounds of butylsilanes required for test purposes was synthesized by reducing butyltrichlorosilane with lithium aluminum hydride in dioxane solution. This was safely and successfully accomplished by operating in steel equipment under an atmosphere of oil-pumped nitrogen to minimize the hazards involved in conducting this operation on a large scale. The apparatus and procedure used to carry out the necessary manipulations are described in this report" (p. 1).

"During the flight investigation of the X-1 airplane the hinge moments of the elevator and aileron control surfaces have been measured over a Mach number range extending to above 1.0. The results of these measurements are presented in this paper" (p. 2).

"Several methods of cyclic de-icing of a gas-heated airfoil were investigated to determine ice-removal characteristics and heating requirements. The cyclic de-icing system with a spanwise ice-free parting strip in the stagnation region and a constant-temperature gas-supply duct gave the quickest and most reliable ice removal. Heating requirements for the several methods of cyclic de-icing are compared, and the savings over continuous ice prevention are shown. Data are presented to show the relation of surface temperature, rate of surface heating, and heating time to the removal of ice" (p. 1).

Investigation of the effect on zero-lift drag of varying the size and number of symmetrically mounted nacelles on a 45 degree sweptback wing and body combination as determined by free-flight tests of rocket-propelled models over a range of Mach and Reynolds numbers. The nacelle configuration consisted of a twin-engine nacelle near the fuselage, a combination of single-engine nacelles at the wing tip and fuselage, a large nacelle at the wing tip, and a large nacelle near the fuselage.

Report presenting combustion-efficiency data for a 5-inch ramjet-type combustor using a simple V-gutter flame holder. Data for homogeneous fuel-air mixtures of 14 pure fuels and 3 fuel blends cover a range of inlet static pressures and velocities.

Motion pictures at camera speeds up to 3000 frames per second were taken of the combustion of liquid oxygen and gasoline in a 100-pound thrust rocket engine. The effect of seven methods of propellant injection on the uniformity of combustion was investigated. The flame front was generally found to extend to the injector faces and all the injection systems showed considerable nonuniformity of combustion. Pressure vibration records indicated combustion vibrations that corresponded to resonant-chamber frequencies.

Report presenting an investigation to determine the static longitudinal stability and control characteristics of a tailless wing-body combination with a pointed wing of aspect ratio 2 and trailing-edge elevons. The effectiveness of inset tabs in reducing the elevon hinge moment was also determined. Results regarding the lift, drag, pitching moment, elevon hinge moment, tab hinge moment, elevon load, and center of pressure of elevon load are provided.

Report presenting an investigation at Mach number 1.61 to determine the hinge-moment characteristics of seven tip controls on a 60 degree sweptback delta wing. Testing occurred over a range of angles of attack and control deflection. The results indicated that the most important parameter in designing delta-wing tip control is the ratio of control-surface area ahead of the hinge line to total control-surface area.

Report presenting an investigation of three different nacelles in an underwing position at the 0.46 semispan station of a 45 degree sweptback wing at three chordwise positions for a range of Mach numbers. The nacelle profiles were an ogive cylinder, an NACA 65A-series airfoil, and an NACA 0-series airfoil (reversed). Results regarding drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.

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.