Report presenting a study of the finite-span effects on the local loading characteristics of two sweptback wings at low speed in order to provide some information about the usefulness of two-dimensional section data and span-loading theory for determining the section characteristics of a swept wing. At low values of lift coefficient, the finite-span effects were restricted to regions of the wing close to the root and tip. Results regarding the local pressure-distribution comparisons, local lift-curve comparisons, and evaluation of surface-loading procedure are provided.

Report presenting the potential of the linearized flow for a lifting-line propeller of arbitrary circulation distribution at subsonic advance as derived in cylindrical harmonics. From the potential the induced angle at the lifting line is obtained.

Report presenting the velocity potential for a triangular wing with subsonic leading edges experiencing harmonic deformations in supersonic flow. The oscillations considered are such that the amplitude of wing distortion can be represented by a general quadratic expression for a surface.

Note presenting the results of an experimental investigation of impact-pressure interpretation in supersonic and subsonic rarefied air streams at a range of Mach and Reynolds numbers.

Note presenting a study of the factors that affect the survival of human beings in airplane accidents followed by fire by conducting full-scale crashes of transport- and cargo-type airplanes. Some of the factors studied include thermal injury, toxic gases, missiles, and structural destruction of occupied compartments are provided.

Report presenting spanwise lift distributions for nineteen unswept wings with various aspect ratios and taper ratios and with a variety of angle-of-attack or twist distributions, including flap and aileron deflections, by means of the Weissinger method with eight control points on the semispan. Also calculated were aerodynamic influence coefficients which pertain to a certain definite set of stations along the span, and several methods are presented for calculating other aerodynamic influence coefficients.

Note presenting an investigation which utilized the statistical methods developed in previous research to study the scatter found in aluminum alloys and the effect of the morphology of the carbide phase on the scatter in a eutectoid steel. The scatter in fatigue life for 24S and 75S aluminum was found to be comparable with that reported previously for steel.

Report presenting experiments to measure the coefficient of friction and to determine the damage to the contact area during early stages of fretting of copper at a frequency of 5 cycles per minute. Specimen combinations of copper against glass, copper against copper, and copper against steel, as well as various copper oxide films and powder compacts were used.

From Introduction: "This report presents a method of representing inlet air-flow capacities by the same parameter used to represent engine air-flow requirements so that the determination of the inlet operation condition at the match point can be simplified. Methods for analyzing the inlet geometric variations required to improve the power-plant performance at the match point are discussed and several examples are presented to illustrate the technique."

Report presenting a two-dimensional wind-tunnel investigation at low speeds of the NACA 64A010 airfoil section equipped with various combinations of a leading-edge slat, leading-edge flap, split flap, and a double-slotted flap. Optimum slat positions and section lift and pitching moment characteristics of the model arrangements were determined for various Reynolds numbers.

Report presenting an investigation of the methods of analyzing longitudinal frequency-response characteristics of aircraft. The methods considered are analysis of sinusoidal response, analysis of transient response to harmonic content through determination of the Fourier integral, and analysis of the transient through the use of least-squares solutions of the coefficients of an assume equation for the transient time or frequency response.

Note presenting the results of a wind-tunnel investigation to determine the effects of moderate amounts of camber on the aerodynamic characteristics of a 10-percent-thick modified NACA four-digit-series airfoil section. The results indicate that the principal effects of increasing camber were an increase in maximum lift coefficient and increases in lift- and drag-divergence Mach numbers at moderate to large lift coefficients.

Note presenting a simplified method developed for the calculation of heat transfer and skin friction in the compressible boundary layer with an arbitrary Prandtl number near unity and an arbitrary streamwise pressure gradient and wall temperature distribution. The method maybe extended to calculation of heat transfer with equilibrium dissociation provided the wall temperature is below dissociation temperatures.

Report presenting an investigation using a twin-engine airplane model in the 300 mph 7- by 10-foot tunnel to determine the magnitude of the changes in aerodynamic forces and moments resulting from propeller pitch reversal. The effects of both positive and negative thrust coefficients were investigated at Reynolds number 550,000. Results regarding the analysis of effects of symmetric and asymmetric thrust on the aerodynamic characteristics and typical performance and control estimates are provided.

Report presenting two 75-millimeter-bore inner-race-riding cage-type ball bearings used in an experimental investigation of the effects of oil inlet temperature and viscosity on bearing operating characteristics over a range of DN values. An increase in oil viscosity produced increased bearing temperatures and caused the power rejected to the oil to be greater with constant DN, load, oil flow, and oil inlet temperature.

A method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, based on a simple momentum balance consideration, permits the computation of inlet pressure recovery - mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound. The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result.

Trajectories were determined for droplets in air flowing through 90 deg elbows especially designed for two-dimensional potential motion with low pressure losses. The elbows were established by selecting as walls of each elbow two streamlines of the flow field produced by a complex potential function that establishes a two-dimensional flow around a 90 deg bend. An unlimited number of elbows with slightly different shapes can be established by selecting different pairs of streamlines as walls. The elbows produced by the complex potential function selected are suitable for use in aircraft air-intake ducts.