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.

The analytical results of Part I are also applied to sound dispersion by friction and heat conduction, An irreversible change of momentum, energy, and type of particle corresponding to friction, heat conduction, and diffusion effects can appear both in the direction of the sound field and traverse to it. Longitudinal damping, the coupling of longitudinal damping and that due to chemical and physical changes, and coupling of diffusion and compositional changes are treated for a plane sound wave of infinite extent.

Memorandum presenting a treatment of the problem of the differential isentropic changes of state in dissociating gases.

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.

Report presenting the low-speed stalling and lift characteristics of the Douglas D-558-II airplane measured in a series of 1 g stalls in four different airplane configurations. Various combinations of landing gear, flaps, inlet-duct flaps, and slats were tested at a range of altitudes.

Report presenting testing using rocket-powered models to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings with thin, symmetrical, double-wedge airfoil sections. The theory compared favorably with experimental results over most of the test range. Taper was generally found to increase wing drag at low supersonic speeds but reduced drag at higher speeds.

Memorandum presenting an investigation of the low-speed static stability characteristics of a canard model with a 45 degree sweptback wing and a 60 degree triangular horizontal control surface. Results regarding longitudinal stability and control and lateral stability and control are provided.

Report presenting a wind-tunnel investigation to determine the low-speed longitudinal and lateral control characteristics of a model with a triangular wing with NACA 65(06)-006.5 airfoil sections, aspect ratio 2.31, and constant-chord control surfaces. The values of the hinge-moment parameters were found to be of somewhat greater magnitude than would be expected on unswept wings with the same aspect ratio.

Report presenting a method for calculating the path of a jettisonable nose section at any speed by means of successive approximations using static aerodynamic characteristics. Conditions for consideration, including the effect of stabilizing fins, are included in the calculations.

From Summary: "Flight tests have been conducted on rocket-propelled models of an airplane configuration incorporating a sweptback wing with inverse taper to investigate the drag, stability, and control characteristics at transonic and supersonic speeds. The models were tested with a conventional tail arrangement in the Mach number range from 0.55 to 1.2. In addition to the various aerodynamic parameters obtained, the flying qualities were computed for a full-scale airplane with the center-of-gravity location at 18 percent of the mean aerodynamic chord. Also, included in this investigation are drag measurements made on relatively simple fixed-control models tested with both conventional and V-tail arrangements."

"Existing conical-flow solutions have been used to calculate the hinge-moments and effectiveness parameters of trailing-edge controls having leading and trailing edges swept ahead of the Mach lines and having streamwise root and tip chords. Equations and detailed charts are presented for the rapid estimation of these parameters. Also included is an approximate method by which these parameters may be corrected for airfoil-section thickness" (p. 937).

Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel with a scale model to determine the spin and recovery characteristics of the McDonnell XF3H-1 airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined. Results regarding design gross weight loading, variation of loading, spin-recovery parachutes, pilot escape, landing condition, control forces, and recommended recovery technique are provided.