Report presenting surface temperature distributions on a hollow cylinder aligned with the airstream was studied in a Mach 3.12 wind tunnel at a range of Reynolds numbers. Transition with and without single roughness elements was observed from surface temperature distributions and high-speed schileren motion pictures. Results regarding pressure distributions, recovery-factor distributions, high-speed schileren motion pictures, transition Reynolds number, heat-conduction effects, and a qualitative description of observed flows are provided.

Report presenting testing of heat-treated cast HS-21 turbine blades to determine the effect on the service life by running the blades to failure in a J33-9 turbojet engine. The heat treatment effects were found to depend on the initial structure of the cast blades. Results regarding engine operation, metallurgical studies of as-cast and heat-treated blades, and metallurgical studies of failed blades are provided.

Because the Weissinger seven-point results were found to be in error for wings combining high aspect ratio with large amounts of sweep, a simple procedure is demonstrated which corrects errors and results in more accurate span loadings read directly from loading charts. The procedure consists of an alteration of the taper ratio used plus an additional correction applied at the wing root.

Report presenting the flow characteristics of a series of rectangular outlets which discharge air into the transonic stream together with wall static-pressure distributions in the vicinity of the outlets, as well as thrust coefficients of rectangular and circular outlets. Results regarding the discharge coefficients, surface pressure distribution, vent pressures, and thrust coefficients are provided.

Report presenting the results of a wind-tunnel investigation of a series of models of nine related horizontal tails to provide basic design information, including the effects of aspect ratio, sweepback, and changes in the Mach number, and to provide experimental values of the lift and hinge-moment parameters for comparison with values computed by a method employing lifting-surface theory.

Results are presented of tests to determine the effect of heating at uniform temperature rates from 0.2 degrees to 100 degrees F per second on the tensile properties of 7075-T6 d(75s-T6) and 2024-T3 (24s-T3) aluminum-alloy sheet under constant-load conditions. Yield and rupture stresses, obtained under rapid-heating conditions, are compared with results of elevated-temperature stress-strain tests for 1/2-hour exposure. Master yield-and-rupture-stress curves based on linear temperature-rate parameter are presented. Yield and rupture stresses and temperatures may be predicted by means of master curves and the parameter.

Report presenting the application of the techniques of generalized harmonic analysis to the airplane taxiing problem. Some previous results on runway roughness are reviewed and some results obtained from taxiing tests of a large airplane are given. The use of spectral techniques was found to be a rather concise way of presenting the characteristics of runway roughness.

Report presenting equations that are extended to include corner effects when evaluating gas-flow interferometry. A simple method for evaluating the density adjacent to a surface is described.

Report presenting a method for estimating the equilibrium operating line for a compressor as a component part of a turbojet engine. Charts are presented for locating the equilibrium operating line on the performance map of the compressor component of a turbojet engine operating at sea-level static conditions. Results regarding design-point operation, off-design operation, effect of compressor-discharge bleed, effect of jet-nozzle adjustment, and an example are provided.

Report presenting an analysis of overall sound-level measurements and frequency analyses of tape recordings of the noise emitted from a 10-foot-diameter, four-blade propeller mounted on a turbine-powered vehicle under static conditions at stations equally spaced on a 75-foot-radius circle. Results regarding the distribution of overall sound-pressure levels and distribution of sound-pressure levels for the first four propeller harmonics are provided.

From Introduction: "The present paper contains a first-order evaluation of a number of aerodynamic derivatives for a rectangular wing of infinite aspect ratio at finite angles of attack, based upon the linear perturbation theory for rotational flow."

Note presenting tables of coefficients which facilitate the stress analysis of circular semimonocoque cylinders with cutouts by the method published in a previous report. When the values of two simple structural parameters are known, use of the coefficients enables shear flows and stringer loads in the neighborhood of a cutout to be calculated.

Report presenting a general matrix method for the solution of characteristic-value problems of the type arising in many physical applications. The matrix is applied to the problem of finding criticality and neutron fluxes in a nuclear reactor with control rods. The two-dimensional finite-difference approximation to the two-group neutron-diffusion equations is treated.

Report presenting a study to investigate some aspects of the nature of the flow around delta wings. Vapor-screen, pressure-distribution, and ink-flow studies on a series of semispan delta-wing models with slender wedge airfoil sections and very sharp leading edges were conducted.

Report presenting the measurement of effective flame speeds of free turbulent flames using photographic, ionization-gap, and photomultiplier tube methods and were found to have a statistical distribution attributed to the nature of the turbulent field.

Report presenting an investigation of toothed attachments to a full-scale turbojet nozzle for possible jet-noise reduction and thrust penalty. The attachments caused slight reductions in total sound power, which are relatively insignificant when compared to the negative effects. Results regarding the sound pressure measurements, frequency spectrum, total sound power and engine thrust, and auditory effects are provided.

Note presenting an analysis of the effects of heat sources and frictional heating on the laminar fully developed channel flow subject to a body force between two parallel plates oriented in the direction of the body force. Solutions are obtained for combined forced- and natural-convection flows for the cases in which the wall temperature variations are linear and the wall temperatures are specified, the walls are both insulated, and the net mass flow in the channel is zero. Results regarding the linear side-wall temperatures and effects of having both side-walls insulated are provided.

The models, apparatus, and instrumentation developed for investigations of the rough-water characteristics of seaplanes in the Langley tanks are described briefly. The results of several investigations to improve these characteristics are combined and summarized. The large effect of waves in take-off resistance is illustrated. The general relationship of the measured quantities of importance to wave length and height are also illustrated.

Report presenting relations for the calculation of heat transfer at the forward stagnation point of both two-dimensional and axially symmetric blunt bodies. The relations for the heat transfer, which were obtained from exact solutions to the equations of the laminar boundary layer, are presented in terms of local velocity gradient at the stagnation point.

Report presenting an investigation using rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack.

Note presenting an investigation of the profiles and thicknesses of normal shock waves of moderate strength in terms of the variation of the equilibrium temperature of an insulated transverse cylinder in free-molecule flow. The shock waves were produced in a steady state in the jet of a low-density wind tunnel, at initial Mach numbers of 1.72 and 1.82 in helium and 1.78, 1.85, 1.90, 1.98, 3.70, and 3.91 in air. Results regarding the free-molecule probe response in a uniform stream, operation of normal shock holders, normal-shock-wave profiles, shock-wave thicknesses, evidence of wire-size effect on shock-wave profile, and the potential of experimental error are provided.

Note presenting an analysis made for laminar free convection on a vertical plate with nonuniform thermal conditions at the surface. Prescribed variations are considered for the wall heat flux and for the wall temperature. Graphs are presented from which the resulting wall-temperature variation may be obtained.

Report presenting the effect of compressibility on the loss characteristics downstream of two-dimensional turbomachine blade rows. In this particular example, increasing the trailing-edge thickness increased the overall loss coefficients significantly, with an effect of compressibility only at exit flow angles close to axial.

Experimental data obtained from three shielded and three unshielded thermocouple probes are presented. Data taken in air at room temperature over the ranges 0.2 to 2.2 Mach number and 0.2 to 2.2 atmospheres total pressure show reproducible systematic variations of recovery with Mach number, ambient pressure, flow angle, and probe design. Time-constant data determined at Mach 0.2 and room temperature and pressure indicate that unshielded probes are several times faster in response to temperature changes than shielded probes.