From Introduction: "A collection balanced-aileron test data is given in reference 1. Reference 2 presents a collection of data applicable to the design of tail surfaces. The results of analyses of data for control surfaces with internal balances, plain-overhang and Frise balances, beveled trailing edges, and unshielded horn balances have already been published in references 3 to 6."

From Introduction: "An analysis of a square web above the buckling load was presented in reference 1. The analysis of reference 1 therefore was repeated for a shear web with depth/width = 2.5. Comparison of the results with those for the square web then would indicate the effect in the depth-width ratio."

From Introduction: "The results of the tests made with unheated internal flow are reported in reference 1. It is the purpose of this paper to attempt to express simply the efficiency loss as a function of the parameters which govern propeller operation and the internal air flow. The derived equations are correlated with the data presented in reference 1."

From Introduction: "The present paper has been prepared to give the results of the analysis of the V-G records obtained from three Boeing S-307 airplanes operating in Caribbean region and the northern part of South America during the period from 1940 to 1944."

From Introduction: "The present report is the second prepared to give the results of an analysis of V-G data from commercial transport airplanes. The present report is concerned with an analysis of data obtained with Douglas DC-3 airplanes flying over three transcontinental routes in the United States."

From Introduction: "It is the purpose of this paper to describe the physical properties that are necessary to specify mixture quality in a system containing fuel and dry air and to evaluate the theoretical rolation between these properties and the physical properties of the mixture."

From Introduction: "Because of the importance of spray height, it is the purpose of the work considered in this report to attempt to determine a correlation for the main spray height in relatively smooth water."

Note presenting a system for calculating the physical properties of supersonic rotational flow with axial symmetry and supersonic rotational flow in a two-dimensional field as determined by use of the characteristics method. Practical use of the system is based on a step-by-step procedure that requires long numerical calculations. Some applications were made to determine the external and internal flow on bodies of revolution with axial symmetry.

Report presenting a number of calculations of bending-torsion wing flutter at two Mach numbers and a comparison of the results. The results indicated that the effect of compressibility on flutter speed for subsonic speeds with no shocks, although complicated, is relatively small in the usual cases.

Report presenting tests of two wings, one stubbed and one regular-sized, in the propeller-research tunnel to determine the increase in lift obtainable by boundary-layer control and to determine the power required for the blower. Lift coefficients of about 3.2 were obtainable for both wings, but the pressure method required several times more power than the suction method.

Report presenting the calculation of surface temperatures for bodies in steady supersonic flight at Mach numbers from 2 to 10, altitudes from 50,000 to 200,000 feet, and emissivites from 0 to 1. The importance of the effects of radiation and convection was determined. Some suggestions for further research into unsolved problems are also provided.

Report presenting a study of accurate values of the specific heat for dry air applied to the calculation of work required to compress dry air. Two charts are provided that allow the work of compression to be determined from the initial temperature, overall pressure ratio, and either the compression exponent or adiabatic efficiency of the compressor.

"A single chart has been prepared that simplifies the calculation of the thermodynamic properties of air, various octene-air mixtures, and mixtures of those with their products of combustion at all temperatures below which chemical dissociation becomes unimportant. The chart is based on the use of 1 pound mol of mixture, and examples of its use are given in the form of the calculation of a turbocompressor power plant and a supercharged Otto engine cycle" (p. 1).

Note presenting a solution for the buckling load and load carried after buckling of a clamped rectangular plate with a width-length ratio of 1:4 under combined normal pressure and axial load. The results indicate that normal pressure causes a smaller increase in the buckling load of plates with clamped edges than of plates with simply supported edges.

Note presenting an investigation of the use of aluminum alloy 14S-T in heavy-duty structural applications and aircraft. The column data presented in this report have been obtained on extruded shapes and on rolled and drawn rod of the alloy.

"Because the tensile strength and tensile yield strength of alloy 75S-T are appreciably higher than those of the materials used in the tests leading to the use of the straight-line column curve, it appeared advisable to establish the curve of column strength by test rather than by extrapolation of relations determined empirically in the earlier tests. The object of this investigation was to determine the curve of column strength for extruded aluminum alloy 75S-T. In addition to three extruded shapes, a rolled-and-drawn round rod was included" (p. 1).

Note presenting an investigation to compare the effectiveness of two basic methods of cooling a turbosupercharger and to obtain data on the temperature level and distribution in the turbine wheel. Turbine-wheel temperatures were obtained for various conditions of cooling-air mass flow, exhaust-gas temperature, and exhaust-gas mass flow. Modified forms of the standard cooling caps were used to allow for the installation of temperature-measuring devices.

Web stresses and flange stresses were measured in three built-up beams: one of constant depth with flanges of constant cross-section, one linearly tapered in depth with flanges of constant cross section, and one linearly tapered in depth with tapered flanges. The measured stresses were compared with the calculated stresses obtained by the methods outlined in order to determine the degree of accuracy that may be expected from the stress analysis formulas. These comparisons indicated that the average measured stresses for all points in the central section of the beams did not exceed the average calculated stresses by more than 5 percent. It also indicated that the difference between average measured flange stresses and average calculated flange stresses on the net area and a fully effective web did not exceed 6.1 percent.

Report presenting knock testing of a sensitive fuel and a relatively insensitive fuel in a full-scale air-cooled cylinder. Six engine variables were investigated: fuel-air ratio, compression ratio, inlet-air temperature, spark advance, exhaust pressure, and cylinder temperature.

Report presenting several methods of predicting the compressible-flow pressure loss across a baffled aircraft-engine cylinder that were analytically and experimentally investigated on a typical air-cooled aircraft-engine cylinder. Results regarding the evaluation of data, comparative accuracy of correction methods, and ability to apply information about heat transfer to compressible-flow pressure-drop predictions are provided.

Note presenting static tests made on machine-countersunk riveted joints in 24S-T, X75S-T, and Alclad 75S-T sheet using A17S-T and 24S-T rivets. In order to intensify the cutting action of the rivets, all specimens were made with the depth of countersink just equal to the thickness of the sheet.

Note presenting pressure distributions and schileren photographs for the high-speed flow about a symmetrical airfoil at zero lift in open and closed jets in order to show the nature of the jet-boundary interference. Results regarding the application of jet-boundary-interference theory, analysis of experimental wall-interference data and comparison with theory, conditions near choking, and change of velocity ratio with Mach number are provided.

"Results are presented for a part of a test program on 24S-T aluminum alloy flat compression panels with longitudinal formed hat-section stiffeners. This part of the program is concerned with panels in which the thickness of the stiffener materials is 0.625 times the skin thickness. The results, presented in tabular and graphical form, show the effect of the relative dimensions of the panel on the buckling stress and the average stress at maximum load" (p. 1).

"Initial shocks of the type that occur on airfoils at stream Mach numbers less than unity are shown to satisfy a certain condition, namely, that the local Mach number behind the shock wave tends to approach unity. This result is, in nature, similar to the classic condition of Kutta on the circulation" (p. 1).