Note presenting a method by which the total temperature of the gases at the combustion-chamber outlet of a ramjet engine may be determined from the loss in total pressure measured across the combustion chamber. Values of total-temperature ratio across the combustion chamber of a 20-inch ram jet were obtained in the altitude wind tunnel over a range of pressure altitudes.

Note presenting an investigation of three ceramic coatings applied to four heat-resistant alloys that are tested for effectiveness in preventing carbon absorption under strongly carburizing conditions (box carburizing).

From Summary: "A literature survey was conducted to determine the relation between aircraft ignition sources and inflammables. Available literature applicable to the problem of aircraft fire hazards is analyzed and discussed herein. Data pertaining to the effect of many variables on ignition temperatures, minimum ignition pressures, and minimum spark-ignition energies of inflammables, quenching distances of electrode configurations, and size of openings incapable of flame propagation are presented and discussed."

"Three-dimensional interaction surfaces are presented for the computation of elastic buckling stresses for an infinitely long flat plate subjected to combinations of bending, shear, and transverse compression in its plane - a loading approximating that occurring in a shear web. Surfaces are presented for two sets of edge conditions: both edges simply supported and lower edge simply supported, upper edge clamped. Present results are in good agreement with data for one-load and two-load limiting cases previously published" (p. 1).

Report presenting three modifications to the leading-edge region of the NACA 64A010 airfoil section, which were designed and tested two-dimensionally at both low and high subsonic speeds. The modifications increased the low-speed maximum lift coefficient of the symmetrical reference section, largely by increasing the angle of attack at which stall occurred.

Note presenting an investigation to determine the effect of spot-weld quality on the corrosion behavior of panels fabricated from alclad 24S-T3, 24S-T3, R-301-T6 of 0.020-inch thickness. The preparation and examination of each of the specimens is described. Results regarding effect of exposure on weld shear strength, effect of exposure on normal tensile strength of welds, and a metallographic examination of spot welds are provided.

Report presenting an investigation of jet flaps in the 300 mph 7- by 10-foot tunnel on an unswept, untapered wing with an aspect ratio of 8.4 and a thickness of 16.7 percent. Results regarding jet flap, jet-augmented trim flap, jet-augmented plain flap, and estimated thrust required for steady flight of an airplane with the jet-flap system are provided.

Report presenting generalized expressions and charts which depend on the shock Mach number, initial state of the gas, and an enthalpy parameter for the temperature, pressure, density, and flow velocity behind a shock wave.

Note presenting the results of a survey of background and aircraft noise levels in residential communities in eight cities with major airports. The measurements were made in areas up to 12 miles away from the airports and were located in regularly used flight paths. The results indicated that there is a range of more than 20 decibels in the average background noise in the 180 areas included in the survey.

From Summary: "Experimental measurements have been made of the zero-lift drag rise at transonic speeds of a family of triangular plan form wings of varying thickness and aspect ratio mounted on a cylindrical body. Together with the transonic similarity parameters, the results of the tests are used to define the range of applicability of the transonic area rule for wings of triangular plan form. The significance of the test results is discussed."

Report presenting a wind-tunnel investigation at low speeds to determine the effect of aspect ratio and end plates on the aerodynamic characteristics of an unswept and untapered wing equipped with jet flaps deflected 85 degrees and operating with momentum coefficients as high as 17.5.

Report presenting calculations of the correlation functions and power spectra of the rolling and yawing moments on an airplane wing due to the three components of continuous random turbulence. Specific numerical calculations are made for a pair of correlation functions given by simple analytic expressions which fit available experimental data.

Note presenting the equations of the compressible laminar boundary layer for the windward streamline in the plane of symmetry of a yawed cone. Solutions are obtained for both insulated and cooled surfaces. The heat-transfer rate to this most windward streamline increases significantly with angle of attack.

Report presenting one-dimensional, steady-state, compressible, viscous flow relations which permit the determination of flow conditions at any radial position in a ducted helicopter blade. The relations are required for estimating the performance of proposed helicopter jet-propulsion systems which involve ducting air or gases through the blade from root to tip.

Note presenting a summary of all phases of an investigation of fretting corrosion that has been conducted over a period of several years. Part I describes a test machine for measuring fretting damage under controlled experimental conditions. Part II presents data for mild steel fretted against itself, with a number of characteristics taken into consideration. Part III suggest a mechanism for the fretting process.

Note presenting the operating characteristics of an acceleration restrictor which limits the normal acceleration of an airplane in maneuvers determined from tests on a simulator. The simulator consisted of a control stick geared to a magnetic brake unit and an analog computer which simulated the dynamic characteristics of the airplane.

From Introduction: "These aerodynamic data were used previously in an analytical investigation of a spin recovery by rudder reversal, the results of which have been published in reference 2. Because of certain discrepancies in the rotary-balance data similar to those discussed in reference 3, some modifications were made to the aerodynamic data used in calculating the results in reference 2 and also the results in this paper; these discrepancies and modifications are discussed in detail herein."

Report presenting an approximate, theoretical analysis of the inlet or induction losses due to subsonic flow into a high-solidity cascade of finite thickness blades at incidence angle. Results indicated that the losses can become considerable for large deviations from the design incidence such as compressor off-design operating conditions. Results regarding the computational results, significance of assumptions and limitations, comparison of theoretical approximation with actual compressor results, and applicability of the results are provided.

Report presenting a theoretical and experimental investigation of heat transfer involving laminar natural convection of fluids enclosed between parallel walls oriented in the direction of body force. The results are presented in the form of equations for the velocity and temperature profiles and ratio of actual temperature drop across the fluid to the temperature drop for pure conduction.

Report presenting a systematic investigation of the sound field of a 1,000-pound-thrust solid-fuel rocket and data on two other rockets of 900 and 5500 pounds of thrust, which were obtained at a few isolated field points. Each of the three rockets was found to produce spectra somewhat similar to those of subsonic jets, which were random and with an envelope which peaks in the lower part of the audible range.

"The problem of increasing the range of supersonic aircraft by the use of twisted and cambered wings is considered, primarily for the purpose of developing a rational method for the selection of a design lift coefficient. Relations and curves are presented from which a suitable selection may be made, depending on the relative importance of maximum range and top speed" (p. 1).

Note presenting fatigue tests performed on notched and unnotched sheet specimens made of 2024-T3 and 7075-T6 aluminum alloys and of SAE 4130 steel. The steel was tested in two conditions: normalized and heat-treated to a tensile strength of 180 ksi. The primary focus was on the life range from 2 to 10,000 cycles.

Report presenting results for a continuation of a research program in the high-speed 7- by 10-foot tunnel to investigate the aerodynamic characteristics in pitch, sideslip, and steady roll of model configurations with variations in wing geometric parameters. This particular report contains aerodynamic characteristics in pitch of wing-fuselage combinations with wings of aspect ratio 4, a sweepback angle of 45 degrees, and three different taper ratios. Results regarding lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratios are provided.

Report presenting an investigation at low speed of the two-dimensional aerodynamic characteristics of a 10.51-percent-thick symmetrical airfoil with area suction near the leading edge. The chordwise extent and distribution of porosity were adjusted in order to obtain a low quantity of suction-air flow for the maximum possible lift. Results regarding the plain wing, wing with various chordwise extents of area suction, wing with area suction from the leading edge to 3-percent chord, boundary-layer measurements, and stagnation location are provided.