Report presenting friction and wear experiments conducted to explore the effects of high temperature, varied chlorine content, sulfur catalysis, and preformation of sulfide films on boundary lubrication with reactive gases. Results regarding sulfur hexafluoride, dichlorodifluoromethane, chlorotrifluoromethane, chlorotrifluorometahne plus sulfur hexafluoride, and dichlorodifluoromethane plus sulfur hexafluoride are provided.

The charts presented give the compressive buckling coefficients for a single-truss-core and a double-truss-core sandwich plate. These charts cover a wide range of sandwich proportions and may be used for sandwiches with unequal faces. They apply to inplane compressive loads acting parallel or perpendicular to the core direction or for various combinations of these loads. (author).

Note presenting hot-wire anemometer measurements of the turbulent shearing stress in a turbulent boundary layer on a yawed flat plate. The measured velocity profiles are used to calculate the shear distribution and the result is compared with the result of experimental shear measurements.

Note presenting experiments conducted to determine the effect of a strong axial magnetic field on the flow of mercury through a circular channel. The magnetic induction was 15,000 gauss, and the channel was a pyrex tube 17-1/4 inches long and 0.027 inch inside diameter. The results indicated that the stabilizing effect occurred only at Reynolds number above 5,000, so that the region of practical applicability seems to be at fairly high Reynolds numbers and when there are only slight disturbances in the flow.

Report presenting over 1000 measured convective heat-transfer coefficients for normal cylinders in subsonic slip flow that have been correlated by using Nusselt number as a function of Reynolds and Knudsen (or Mach) numbers. A complicated nonlinear dependence of the heat-transfer coefficient to the difference between cylinder and recovery temperature is reported. The application of these results to hot-wire anemometry is also discussed.

Ram-jet cycles that use the chemical energy of dissociated oxygen for propulsion in the ionosphere are presented. After a review of the properties and compositions of the upper atmosphere, the external drag, recombination kinetics, and aerodynamic-heating problems of an orbiting ram jet are analyzed. The study indicates that the recombination ram jet might be useful for sustaining a satellite at an altitude of about 60 miles. Atmospheric composition and recombination-rate coefficients were too uncertain for more definite conclusions. The ram jet is a marginal device even in the optimistic view.

"The reflection and transmission coefficients have been determined for a plane sound wave incident on a slotted wall separating two moving fluid streams. This acoustics problem is related to the aerodynamic problem of determining the tunnel-wall interference on an oscillating airfoil in a slotted-throat wind tunnel in that the same boundary condition is involved with one of the two streams at the boundary having zero velocity. In the analysis the wall with discrete slots is replaced by an equivalent homogeneous boundary" (p. 1).

"Theoretical buckling stresses are determined in explicit form for circular cylinders with circumferential and axial stiffening. The loadings are axial compression, radial pressure, hydrostatic pressure, and torsion. Analyses were confined to moderate-length and long cylinders" (p. 1).

"A comprehensive review of failure of stiffened curved plates and shells is presented. Panel instability in stiffened curved plates and general instability of stiffened cylinders are discussed. The loadings considered for the plates are axial, shear, and the combination of the two. For the cylinders, bending, external pressure, torsion, transverse shear, and combinations of these loads are considered" (p. 1).

Note presenting heat-transfer and skin-friction parameters obtained from exact numerical solutions to the laminar compressible-boundary-layer equations for the infinite cylinder in yaw. The results indicate that compressibility effects become important at large Mach numbers and yaw angles, with larger percentage effects on the skin friction than on heat transfer.

Note presenting analytical results obtained for boundary-layer mass flow, momentum, total-temperature, and total-pressure recovery ratios of a scoop inlet with a height equal to the boundary-layer thickness and operating in a turbulent boundary layer, for flat and conical surfaces with wall cooling. The results indicate that design of boundary-layer intake devices or diverters must reflect the effects of wall cooling by either variable or compromised size.

Note presenting a study of aluminum alloy containing 4 weight percent copper during aging using low-frequency internal-friction measurements in torsional and flexural vibration. Both polycrystalline and single-crystal specimens exhibit an initial internal-friction peak at 173 degrees Celsius after solution treatment and quenching.

"Results are presented of an investigation to determine the effect of boundary-layer displacement and leading-edge bluntness on surfaces in hypersonic flow. The presence of the boundary layer and the blunt leading edge induce pressure gradients which in turn affect the skin friction and heat transfer to the surface. Methods for predicting these phenomena on two-dimensional surfaces are given and a brief review of recent three-dimensional results is presented" (p. 1).

Note presenting a comprehensive review on the method of split rigidities. The principles on which the method is based are discussed and it is shown how these principles are applied. The method is applied to several examples of using this method to calculate buckling stresses of structures that buckle in composite modes.

From Introduction: "The many physical processes which occur simultaneously in rocket combustion make the entire process extremely complex (ref. 1). The combustion chamber length required for evaporation of liquid-propellant sprays has already been studied (refs. 2, 3, and 4)."

A study of the probable causes of deterioration of each of several adhesives in bonds to stainless steel at temperatures from 400 degrees to 550 degrees Fahrenheit. Preliminary studies of aluminum surfaces on which ions of metal used in stainless steel were introduced showed that iron was probably catalyzing a thermal deterioration of the adhesive. Results regarding the studies of adhesive bonds to aluminum surfaces and studies of adhesive bonds to stainless-steel surfaces are provided.

Report presenting an investigation with two purposes: to obtain a simplified calculation technique for replacing complicated automatic computer calculations and to obtain experimental data for single droplets vaporizing at pressures greater than 1 atmosphere and to check the histories against experimental data.

Report presenting a simplified method that has been devised for the determination of the critical height of three-dimensional roughness particles required to promote premature transition of a laminar boundary layer on models of airplanes or airplane components. Results regarding the calculation of critical roughness height, minimization of roughness drag, limitations, and simplifying considerations are provided.

Note presenting a simplified method for determination of the critical height of three-dimensional roughness particles required to promote premature transition of a laminar boundary layer on models of airplanes or airplane components in a wind tunnel with zero heat transfer. The method has been applied to various types of configurations in several wind-tunnel investigations.

"The momentum integral equations are derived for the boundary layer on an arbitrary curved surface, using a streamline coordinate system. Computations of the turbulent boundary layer on a slightly yawed cone are made for a Prandtl number 0.70, wall to free-stream temperature ratios of 1/2, 1, and 2, and Mach numbers from 1 to 4. Deflection of the fluid in the boundary layer from outer stream direction, local friction coefficient, displacement surface, lift coefficient, and pitching-moment coefficient are presented" (p. 1).

Report presenting heat-transfer measurements made in turbulent flow at a variety of Mach and Reynolds numbers through the use of an axially symmetric annular nozzle consisting of an inner shaped center body and an outer cylindrical sleeve. The results are presented as Stanton number and recovery factor as a function of Reynolds number. Stanton number was found to decrease with an increase in Reynolds number and usually decreases with an increase in Mach number.

Report presenting comparison of transition locations for an open-nose cone, a conventional sharp cone, and a hollow cylinder showed that transition locations on the open-nose cone and hollow cylinder were identical but differed from the sharp cone. Bluntness effects on the open-nose cone were quite similar to those observed on the hollow cylinder.

Report presenting an investigation to determine the effect of single and multiple two-dimensional roughness elements on the temperature distribution, pressure distribution, and heat transfer at Mach 3.1. Results regarding recovery temperatures and heat transfer are provided.

Report presenting studies of some of the effects of parameters such as Mach number, blade angle, and structural damping on the flutter of model helicopter rotor blades in the hovering condition. Forward movement of the blade chordwise center-of-gravity location tended to raise the flutter speeds at low pitch angles, but had no effect at high pitch angles. The significant flutter data for the tests along with detailed descriptions of the models are included to facilitate more detailed analyses.