Report presenting an analysis of the effect at design condition of inlet hub-tip-radius ratio and mass flow per unit frontal area on the allowable rotor-tip speed, pressure ratio, and power input per unit frontal area of multistage axial-flow compressors with approximately symmetrical velocity diagrams at all radii, constant total enthalpy along the radius, a maximum Mach number of 0.8 for all stages, and a prescribed empirical turning limitation. The analysis indicated that for any given hub-tip-radius ratio, the design rotor speed and pressure ratio per stage decrease with increasing design mass flow per unit frontal area.

Report presenting pressure distributions calculated for some symmetrical wing-body combinations at zero lift. Of particular interest is the effect of indenting the body on the distribution of pressure over the wing.

Report presenting a theory and method for the application of interferometry to the measurement of certain two-dimensional gaseous density fields. The theory includes the effects of optical refraction on the observed interference pattern.

Note presenting an elastic-deflection theory for anisotropic plates which exhibit coupling between bending and stretching. The theory provides a basis for analyzing plates integrally stiffened on one side. Example calculations show that in the case of a simply supported square plate loaded in compression and with equal flexural stiffnesses in the principal directions, coupling may significantly lower the in-plane compressive load at which deflections grow rapidly.

From Summary: "A method is presented for obtaining three-dimensional unsymmetric supersonic nozzles and inlets from known axisymmetric flows. Stream-lines bounding the desired exit shape are traced through the known basic flow solution to give the required unsymmetric wall contours. Several examples are given."

Note presenting a transformation theory of systems of partial differential equations which allows the construction of classes of pressure-density relations depending on parameters for which the equations governing the flow can be transformed into an essentially simpler form, into the system corresponding to the wave equation in the subsonic region, and finally into the form corresponding to the Tricomi equation in the transonic region.

Report presenting an analysis of the heat transfer between an insulated tube and the fluid moving through the tube for three inlet fluid conditions: one with constant fluid temperature, one with the temperature decreased exponentially, and one with the temperature decreasing linearly with time. Results regarding the correlation of computed and experimental temperatures, multiple-tube bundle, and single insulated tube are provided.

Investigation of the aerodynamic drag of several jet noise suppressors over a range of Mach numbers and several nozzle pressure ratios. The least drag was caused by lobe-type suppressors. The eight-lobe nozzle with ejector caused the greatest amount of drag.

Note presenting a review of the present and future trends of rolling-contact bearings for aircraft gas-turbine engines, which indicates that while rolling-contact bearings are satisfactory for present production engines, new bearings for future, higher output aircraft engines require more development. These new engines have operating conditions resulting in two primary problems: cage materials and endurance of materials for raceways and rolling elements.

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.

Report presenting the description and characteristics of two small temperature recorders suitable for flight use. One recorder is an electro-mechanical followup, self-balancing potentiometer type and one obtains self-balance by using an electronic feedback amplifier.

Note presenting the spontaneous ignition temperatures of eight structurally different hydrocarbons, which were correlated with the behavior of the same hydrocarbons toward vapor-phase oxidation. The results indicated that reducing the stoichiometry of a hydrocarbon-oxygen gas mixture to less than unity decreases the extent of oxidation, other conditions remaining unchanged.

From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 10 (10 percent thick) in flight through a droplet field were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid varies considerably and under some conditions may be several times the free-stream concentration. Curves of the local concentration factor as a function of spatial position were obtained and are presented in terms of dimensionless parameters that describe flight and atmospheric conditions."

Report presenting testing of a model with heavy beam loadings and an angle of dead rise of 0 degrees subjected to smooth-water impacts at a range of fixed trims and flight-path angles. Results regarding the time histories of horizontal and vertical displacements, vertical velocity, vertical acceleration, and pitching moment are provided.

Report presenting force and moment data obtained at low speeds to determine the aerodynamic characteristics of an unswept untapered semispan wing of NACA 64A010 section and aspect ratio 3.13 equipped with 25-percent-chord unsealed plain flaps with various spans and spanwise locations. Lift, drag, pitching-moment, and flap hinge-moment data were obtained for the wing with the flaps deflected up to 60 degrees.

Report presenting an investigation of the possibility of designing a fixed total-pressure tube which will remain insensitive to inclination of the air stream over a wide range of angle of attack through subsonic and supersonic speed ranges.

Report presenting the development of an exact theoretical method that permits the determination of the pressure field of a wing-body combination with a circular body and a wing with supersonic leading and trailing edges. Detailed calculations were performed for wing-body combinations composed of rectangular wings mounted at incidence on bodies at zero angle of attack for effective chord-radius ratios of 4 or less.

From Summary: "The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4 x 10(exp 6) and 12 x 10(exp 6), respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good."

Presents zero-lift drag data of an NACA RM-10 slender body of revolution with and without stabilizing fins attached. The results from several wind tunnels and in flight are compared. The results cover a Reynolds number range from about 1 time 10 to the 6th power to 40 times 10 to the 6th power for the flight models. The Mach numbers covered include 1.5 to 2.4 in the wind tunnels and 0.85 to 2.5 in flight.