From Summary: "Free-flight tests have been made to investigate the total drag and base drag at different Reynolds numbers of full-scale and half-scale models of an NACA research model designated the RM-10. The general shape of the body was a parabola of revolution of fineness ratio 12.2 with a blunt base to provide space for the rocket jet. The models were stabilized by four 60 degree sweptback fins mounted at the base of the bodies."

Note presenting data obtained for the viscosity corrections to cone probes in supersonic rarefied air flow at a nominal Mach number of 4. The test models consisted of a set of seven geometrically similar 5 degree semivertex-angle cones. Results regarding cone surface pressure distributions, calibration data for geometrically similar cones, orifices size effect, and tests at other Mach numbers are provided.

Report presenting an investigation to study the influence of size, particularly notch-size effect, on extruded 75S-T6 aluminum-alloy test specimens under rotating bending. Results regarding fatigue strength and fatigue-notch factor are provided.

Report presenting the results of tensile and compressive stress-strain tests at temperatures up to 1200 degrees Fahrenheit for SAE 4340, Hy-Tuf, Stainless W, and Inconel X sheet materials which were heat treated to provide ultimate tensile strengths at room temperatures. Tensile and compressive stress-strain curves are given for each material at test temperatures.

Report presenting an evaluation of a prototype instrument designed to give an immediate indication of loss in airplane acceleration due to power deficiency or increased resistance at any time during take-off when the pilot has a choice of continuing or stopping. Proper functioning of the instrument requires that the attitude angle of the airplane should not vary substantially during the part of take-off of interest. The instrument was tested in three types of airplanes and was found to be satisfactory.

Still and motion pictures were made of boundary-layer and wake secondary-flow phenomena visualized by smoke. Two annular cascades of turbine nozzles were used, both designed for constant discharge angle but differing in blade shape and suction-surface velocity distribution. Flows were similar to those obtained with pressure and angle measurements at near-sonic airspeeds. Boundary-layer cross-channel and trailing-edge radial flows caused vortices and an accumulation of low-momentum air at the hub, which may affect flow in following blade rows. Motion of a downstream rotor blade row produced pulsations in trailing-edge radial flow. The motion-picture supplement may be obtained on loan from NACA Headquarters, Washington, D.C.

Note presenting a method for determining the time-dependent flow over a rectangular wing moving with a supersonic forward speed and undergoing small vertical distortions expressible as polynominals involving spanwise and chordwise distances. The solution for the velocity potential is presented in a form analogous to that for steady supersonic flow with the familiar "reflected area" concept.

From Introduction: "The present paper employs an approach believed to be novel in slender-body theory and is concerned with developing formulas for the forces and moments as well as the stability derivatives for slender wing-body combinations."

"Measurements of actual runway roughness obtained by a profile-survey method (engineer's level) are presented. Data were obtained from a survey of a relatively rough runway and a smooth runway. The results of this study are presented as roughness profiles of the runways surveyed and in the form of power spectra" (p. 1).

Note presenting pressure measurements on the surface of a two-dimensional symmetrical double-wedge airfoil obtained from tests in the Langley 4- by 19-inch semiopen tunnel at lifting conditions and Mach numbers up to 1. The purpose of the investigation was to obtain normal-force, pressure-drag, and pitching-moment data and to compare them with available experimental and theoretical results.

Report presenting an investigation of aeroelastic instability phenomena of isolated open and closed rigid bodies of revolution free to move under elastic restraint at low speeds. Results regarding speeds at which flutter or divergence occurs, the flutter-speed coefficient, and speed coefficients are provided.

Report presenting the results of an investigation to determine the static strength and creep behavior at elevated temperatures of seven nominally identical multiweb box beams made of 24S-T3 aluminum alloy. The analytical and experimental results agreed well.

Note presenting the rate of local heat transfer from a solid surface to a moving fluid as related to the local skin friction. This report discusses the possible range of a particular instrument in low- and high-speed flow and presents experimental data to show that a very simple instrument can be used to obtain laminar and turbulent skin-friction coefficients with a single calibration.

Report presenting a general Rayleigh analysis in order to develop four methods of flutter analysis that are applied to twelve low-aspect-ratio wings. The four methods of flutter analysis used are section coefficients for harmonically pitching and translating rectangular wings in a Rayleigh type of analysis, two-dimensional coefficients in a Rayleigh type of analysis, total coefficients for harmonically pitching and translating rectangular wings in a representative-section analysis, and two-dimensional coefficients in a representative-section analysis.

Report presenting tunnel testing of the flutter of 12 widely different unswept cantilever wings with a variety of mass-density parameters, center-of-gravity positions, and elastic-axis positions. Results regarding the flutter parameters, flutter-speed coefficients, effect of airfoil-section shape on flutter, and aspect-ratio effects are provided.

Report presenting a calculation of the power spectrum of relatively short wavelength turbulence in the atmosphere using measurements made in flight. The power spectral density varies with the square of the wavelength of the turbulence. Results regarding the power spectrum of gust vertical velocity, problems related to gust disturbance determination, and use of flow-direction vanes are provided.

Report presenting an investigation of the flow field behind a single rotor and a tandem rotor in the full-scale tunnel at a tip-speed ratio of 0.15. A chart of the flow angles and dynamic-pressure contours behind the single rotor is presented. Comparisons indicate that theory is sufficiently accurate for use in preliminary design calculations and that the flow behind a rotor is very much like the flow behind a wing.

Note presenting a simple technique for correcting the results of thin-wing theory near round or sharp edges at which the normal component of free-stream velocity is subsonic. The flow in planes normal to such edges is actually brought to rest, but thin-wing theory instead predicts infinite velocities.

Note presenting results of a study of the area effect in 24S aluminum alloy. The area effect refers to the phenomenon whereby small areas show long times to failure while large areas show short times. The effects of stress level, degree of sensitivity of the alloy, and hydrogen peroxide concentration in the corrosion medium were studied.

From Introduction: "The present paper employs an approach believed to be novel in slender-body theory and is concerned with developing formulas for the forces and moments as well as the stability derivatives for general slender wing-body combinations."