"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).

Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.

Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.

Report presenting a consideration of the problem of shaping an adjoining fuselage for a given wing and supersonic Mach number so that the combination will have a low wave drag. Only fuselages that can be simulated by singularities distributed along the body axis are studied.

Memorandum presenting the Bell X-5 research airplane tested at 58.7 degrees sweepback during the program to determine the characteristics of a variable-sweep fighter airplane at transonic speeds. This paper includes the stability and control characteristics in the stable lift range up to Mach numbers near 1.0 at an altitude of 40,000 feet and to slightly lower Mach numbers at altitudes of 25,000 feet and 15,000 feet. Results regarding general comments, static stability and control characteristics, and longitudinal dynamic stability are provided.

"The effects of interaction between a landing gear and a flexible airplane structure on the behavior of the landing gear and the loads in the structure have been studied by treating the equations of motion of the airplane and the landing gear as a coupled system. The landing gear is considered to have nonlinear characteristics typical of conventional gears, namely, velocity-squared damping, polytropic air-compression springing, and exponential tire force-deflection characteristics. For the case where only two modes of the structure are considered, an equivalent three-mass system is derived for representing the airplane and landing-gear combination, which may be used to simulate the effects of structural flexibility in jig drop tests of landing gears" (p. 619).

"A general matrix method is developed for the solution of characteristic-value problems of the type arising in many physical applications. The scheme employed is essentially that of Gauss and Seidel with appropriate modifications needed to make it applicable to characteristic-value problems. An iterative procedure produces a sequence of estimates to the answer; and extrapolation techniques, based upon previous behavior of iterants, are utilized in speeding convergence. Theoretically sound limits are placed on the magnitude of the extrapolation that may be tolerated" (p. 747).

Report presenting an investigation of the blades of an experimental two-blade jet-driven helicopter when subject to a condition of near resonance between the frequencies of the first elastic bending mode of the blades and third harmonic component of the aerodynamic loading that results in high bending strains in normal flight conditions. Various changes in design configuration on the blade bending strains were explored. Results regarding the preliminary studies, effects of variation in flight conditions and blade configuration, and harmonic analysis are provided.

Note presenting an experimental investigation of the heat-loss characteristics of heated fine wires suitable for use as anemometers in turbulence research. The effects of each of the several variables on the heat-loss characteristics of both normally oriented and swept wires were measured. The temperature-loading effects were found to cause large sensitivity differences between constant-temperature and constant-current operation.

Note presenting wind-tunnel tests to ascertain the total-pressure recovery of a circular nose inlet utilizing various shapes of inlet lips. The tests were conducted at a free-stream Mach number of 0.237 with inlet flows ranging from low values to choking and at angles of attack from 0 to 25 degrees.

Report presenting a free-flight test technique that can be used to obtain damping in roll of sting-mounted wings and wing-fuselage combinations over high subsonic, transonic, and supersonic speeds with rocket-propelled test vehicles. Results regarding delta wings and unswept tapered wings are provided.

Note presenting a new approach to the theory of the mixing of two currents in an injector which deals with an incompressible ideal fluid. The theory shows new potentialities in an appropriate shaping of the form of the walls of the mixing zone so as to improve the jet-syphon efficiency beyond the heretofore theoretically predicted. A few examples of ways to improve jet-syphon efficiency are indicated.

Report presenting an investigation to determine the shear strengths of high-temperature-alloy blazed joints. The variables investigated included the method of brazing, nickel addition to the brazing alloy, brazing temperature, holding time at temperature, and a protective coating on the braze area for salt-bath specimens. Results regarding individual phases and the microstructure of brazed joints are provided.

From Introduction: "Most of the existing analyses for turbulent flow and heat transfer in passages have been confined to circular tubes or parallel plates (refs. 1 to 5). In reference 6, temperature distributions for rectangular and triangular ducts were calculated by using experimental velocity distributions and average heat-transfer coefficients. Some work on the calculation of the velocity and shear-stress distributions in corners is reported in reference 7."

Note presenting an investigation of screens placed transversely across the jet as a noise-reduction device on a full-scale turbojet engine to determine the effect on the sound field of screen mesh, wire diameter, and screen location. The investigation showed that the screens, when properly placed, lower the noise level in the area downstream of the jet exit and increase it upstream.

Report presenting measurements of the longitudinal turbulent spectra for four stations in a turbulent boundary layer with increasing adverse pressure gradients in tabular form. Frequency diagrams show a decrease in the percentage of energy density contained in the high-frequency range as the flow continued downstream against an adverse pressure gradient.

Technical note presenting tests conducted to determine the factors influencing the thermal conductance across the interface formed between stationary plane surfaces of 75S-T6 aluminum-alloy and AISI Type 416 stainless-steel blocks. The types of joints investigated included bare metal-to-metal contact, contact surfaces separated by a good conductor (brass), and contact surfaces separated by a thin sheet of insulation (asbestos). Results regarding the effect of surface roughness, pressure, mean interface temperature, temperature drop, sandwich material, time as a factor in conductance, and effect of test reassembly and interface matching are provided.

Note presenting an analysis of the problem of shock-induced turbulent boundary-layer separation by an approximate method. The method is based on a moment-of-momentum equation and calculates the change of boundary-layer-thickness parameter sand form factor caused by a discontinuity where the effects of friction can be neglected. The form of the result suggests that the Mach number ratio across the shock is a characteristic parameter for defining shock-induced separation.

Report presenting a simplified procedure to calculate the 1-P oscillating aerodynamic thrust loads on single-rotation propellers in pitch at zero yaw on tractor airplanes. The application of the procedure requires only a knowledge of upflow angles at the horizontal center line of the propeller disk.

"A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).

Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holder.

Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.

Report presenting calculations of the lateral response to representative time histories of atmospheric turbulence for two airplanes with widely different dynamic properties and explanations for their differences in behavior. The results indicate that atmospheric turbulence can cause and maintain a lateral hunting oscillation of a plane, which can be fairly regular and more pronounced for lightly damped airplanes. This may explain some of the cases of airplane snaking that have not been explained by other causes.

Note presenting a series of vitreous coatings of the same basic composition, but with cobalt-oxide contents varying from 0 to 6.4 percent by weight, which was fired on ingot iron in atmospheres consisting of various oxygen-nitrogen mixtures. Results of the investigation showed that a decrease in the amount of oxygen in the firing atmosphere necessitated an increase in the amount of cobalt oxide in the enamel if optimum adherence was to be secured.