Report presenting an investigation to determine the damping-in-pitch characteristics of four rocket-powered wing-body combinations for a range of Mach numbers from 0.85 to 1.30. The models were tested at the same center-of-gravity location and had identical bodies. Information about the trim, lift, static longitudinal stability, dynamic longitudinal stability, and drag is provided.

Report presenting an investigation to determine the pressure drag of various blunt-based conical afterbodies at a range of Mach numbers. A generalized series of bodies was included which incorporated convergent nozzles discharging unheated jets at various pressures from the base. Results regarding the afterbodies without the jet and afterbodies with the jet are provided.

Report presenting an investigation of the effects of leading-edge camber without twist on an aspect-ratio-3 delta wing of thickness ratio 3, a body with an ogive nose, and a cylindrical afterbody. Results regarding the base pressures and body characteristics and wing-body combinations are provided.

Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distribution at six spanwise stations on a 45 degree sweptback, untapered vertical tail in sideslip. The presence of the horizontal tail slightly increased the value of section normal-force coefficients on the vertical tail but did not materially alter the nature of the load distribution.

Report presenting an investigation conducted in the 8- by 6-foot supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Data were obtained for various ejector diameter and spacing ratios at a range of Mach numbers, pressure-ratio ranges, and secondary-primary weight-flow ratios. Results regarding the primary-nozzle mass-flow coefficients, performance comparison of configurations, effect of free-stream Mach number on the ejectors, net thrust characteristics, and comparison to conventional nozzles are provided.

Memorandum presenting the carpet-plotting technique as a more useful and concise method of summarizing the 65-series compressor-blade cascade data. Four different carpet plots are presented. A sample use of the carpet plots is also provided.

"The external wave drag of bodies of revolution moving at supersonic speeds can be expressed either in terms of the geometry of the body, or in terms of the body-simulating axial source distribution. For purposes of deriving optimum bodies under various given conditions, it is found that the second of the methods mentioned is the more tractable. By use of a quasi-cylindrical theory, that is, the boundary conditions are applied on the surface of a cylinder rather than on the body itself, the variational problems of the optimum bodies having prescribed volume or caliber are solved" (p. 131).

Report presenting an investigation in the supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Results indicated that the free-stream Mach number had no effect on those characteristics of the ejectors in the range for which the secondary flow was choked.

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.