From Introduction: "This investigation provides general information on the magnitudes and directions of the aerodynamic forces and moments acting on a fighter airplane in fully developed spins. The investigation includes the determination of the effects on the aerodynamic forces and moments of varied rudder setting with and against the spin, of tail modifications, and of deflected flaps and lowered landing gear."

"The first basic problem that must be solved before control synthesis can proceed is that of determining the dynamic characteristics of the engine. Accordingly, an analysis of the dynamic behavior of the turbojet engine with tail-pipe burning was made at the NACA Lewis laboratory and is presented herein" (p. 1).

From Introduction: "The design of turbojet-engine control systems is intimately related to the dynamic characteristics of the engine and has advanced to the stage where theoretically correct control constants can be determined for fixed dynamic properties (references 1 and 2). The use of the thermodynamic equations presupposes that the engine processes are quansi-static. Such an assumption is shown to be valid for a turbojet engine in references 3 and 4.

Report presenting a metallographic study of the interface between various elements and titanium carbide. Hardness measurements of the different elemental combinations are also provided.

Report presenting the design, development, and performance of equipment suitable for use by educational institutions for student training and basic compressible-flow research. Supersonic nozzles designed for a range of Mach numbers were tested in the blowdown tunnel and produced average Mach numbers close to the design values.

Report presenting an investigation of the effectiveness of molybdenum disulfide as a fretting-corrosion inhibitor. Six methods of applying MoS2 to steel specimens was evaluated by noting the number of cycles of vibration required to produce the first evidence of fretting corrosion and by observing the nature of its occurrence. Experiments were conducted with steel balls vibrating in contact with glass flats whereby the action could be microscopically observed.

"Five stiffened circular cylinders were tested to failure under various combinations of torsion and compression. The results of the tests are presented in the form of plots of stringer stress against cylinder load and an interaction curve for the strength of stringers that fail by local crippling. A method is given for calculating stiffener stresses in cylinders subjected to combined loads, and a comparison between calculated and experimental stringer stresses is made" (p. 1).

Report presenting flow surveys made in a nozzle investigated in the 11-inch hypersonic tunnel. The nozzle was designed for a Mach number of 6.98 and was tested using a two 2-dimensional steps to gradually expand the air in the horizontal and vertical planes. The flow in the test was not sufficiently uniform for quantitative wind-tunnel test purposes.

Report presenting the experimental frequency-response characteristics of engine speed for a typical turbine-propeller engine. The data were obtained by subjecting the engine to sinusoidal variation of fuel flow and propeller-blade-angle inputs. A comparison of the analytical and experimental results is provided.

Report presenting charts by which the jet pressure ratio that gives optimum division of power between propeller and jet for maximum total thrust power may be determined for any turbine-propeller engine with or without intercooling, reheat, regeneration, or any combination of the three modifications. The method of obtaining optimum power division is compared for two sets of conditions with two other methods that have been widely used.

Report presenting a method for convenient determination of the pressure drop sustained by air flowing at high subsonic speeds in a constant-area passage under the simultaneous influence of friction and heat addition. Air-pressure-drop working charts based on the method are presented.

Note presenting a temperature-measuring device using sonic-flow orifices and a comparison with existing temperature-measuring instruments. The device was compared with a standard shielded thermocouple in the temperature range from 710 to 1160 degrees R and excellent agreement was obtained. Limitations and sources of errors of the device are discussed.

Report presenting a survey of the air flow at the plane of the propeller of a full-scale twin-engine airplane to provide data for use in the calculation of oscillating aerodynamic loadings on propellers. The investigation was conducted through a range of angles of attack for two nacelle inlet mass-flow ratios. Results regarding the upwash characteristics and effect of the flow field on the oscillating aerodynamic loading on a propeller are provided.

Note presenting a survey of data from investigations of axial-flow-compressor inlet guide vanes with circular-arc, constant-thickness sections and axial air inlet to establish a relation between vane camber and air turning angle for use in the design of this type of vane. Results regarding design rules for convergent annuli, example of the straight-line rule, design rule for constant axial velocity, and the comparison and use of design rules are provided.

From Introduction: "This paper is concerned with the derivation of expressions for the velocity potential and associated forces and moments for oscillating triangular wings in supersonic flow."

From Introduction: "The present paper is intended to give some features of flutter in bending alone and contains results of analyses made to determine some effects of wing mass-density ratio, angle of sweepback, length-semichord ratio, and Mach number. Some relations of pure-blending flutter to the conventional bending-torsion flutter are also given."

From Introduction: "This report covers three phases of investigation of the problem of improving take-off performance by use of flaps."

From Introduction: "The NACA Lewis laboratory has undertaken a program of analytical study to evaluate the effect on turbojet-engine performance of extracting energy from several points in the cycle. The program included an investigation of the effects of air bleed from the compressor outlet, hot gas bleed from the turbine inlet, hot gas bleed from the turbine outlet, and shaft power extraction (references 1 to 4). "

"An investigation of the heat transfer from an airfoil in clear air and in simulated icing conditions was conducted in the NACA Lewis 6- by 9-foot icing-research tunnel in order to determine the validity of heat-transfer data as obtained in the tunnel. This investigation was made on the same model NACA 65,2-016 airfoil section used in a previous flight study, under similar heating, icing, and operating conditions. The effect of tunnel turbulence, in clear air and in icing was indicated by the forward movement of transition from laminar to turbulent heat transfer" (p. 1).

Note presenting an experimental investigation in which measurements were made of the turbulent boundary layer of a two-dimensional unswept wing and a comparable wing swept 45 degrees. The results indicate the applicability of simple sweep theory for determining turbulent boundary-layer growth on the swept wing for a lift coefficient of zero.

Report presenting a theoretical investigation to determine the effect on the lateral stability of a typical high-speed fighter airplane of an autopilot sensitive to yawing velocity. The effects of inclination of the gyro spin axis to the flight path and of time lag in the autopilot were also determined. The damping of lateral oscillation of the airplane for all flight conditions studied should satisfy the Air Force-Navy criterion when the proposed autopilot is installed.

"An empirical method for the determination of the area, rate, and distribution of water-drop impingement on airfoils of arbitrary section is presented. The procedure represents an initial step toward the development of a method which is generally applicable in the design of thermal ice-prevention equipment for airplane wing and tail surfaces. Results given by the proposed empirical method are expected to be sufficiently accurate for the purpose of heated-wing design, and can be obtained from a few numerical computations once the velocity distribution over the airfoil has been determined" (p. 1).

Report presenting force, moment, pressure-distribution, and boundary-layer measurements for a series of five airfoil sections. The stalling characteristics of the three airfoil sections at low speeds can be separated into three types. A deeper discussion of the role of boundary-layer flow and separation processes in relation to stalling and the sensitivity of stall to factors that influence boundary-layer growth is provided.

Report presenting an experimental investigation of the pressure distribution about a circular cylinder at yaw angles of 0, 15, 30, 45, and 60 degrees and a variety of Reynolds numbers. Testing indicated that for the range of Reynolds number near and above the critical value, the flow and force characteristics of a yawed circular cylinder cannot be determined only by the component of flow normal to the axis of the cylinder.