Note presenting an investigation of the transfer of heat from a metallic ribbon to water, under transient conditions, for initial water temperatures from 76 to 203 degrees Fahrenheit and average heat-generation rates per square foot of square area of 3, 10, and 20x10(exp 5) Btu per hour per square foot. Results regarding the nucleate boiling region, film boiling region, and critical heat flux are provided.

Report presenting an investigation in which upflow angles were measured along the horizontal center lines of the propeller planes of a semispan model representing a multiengine airplane with tractor propellers. Testing occurred at a range of Mach and Reynolds numbers. Results regarding the theoretical methods and a comparison of experimental and theoretical results are provided.

Report presenting the results of flight tests with several typical light aircraft. Flight tests were made with one airplane with two different horizontal tail configurations in an attempt to provide an arrangement that would give optimum conditions with regard to the effect of power change on longitudinal trim near the stall. The results are intended to provide quantitative flight-test information which may be useful to designers in attempting to provide for adequate low-speed control and which may be correlated with analytical analyses.

"Some insight into the range of applicability of the transonic area rule has been gained by comparison with the appropriate similarity rule of transonic flow theory and with available experimental data for a large family of rectangular wings having NACA 63AXXX profieles. In spite of the small number of geometric variables available for such a family, the range is sufficient that cases both compatible and incompatible with the area rule are included" (p. 1).

Report presenting pressure distributions calculated for some symmetrical wing-body combinations at zero lift. Of particular interest is the effect of indenting the body on the distribution of pressure over the wing.

Note presenting some analytical means by which designers may estimate the elevator deflection required to trim in steady longitudinal flight and to demonstrate in a quantitative manner the effects on longitudinal trim of changes in some of the more important design parameters. The procedures can result in a design in which the maximum up-elevator deflection can be maintained within the highest value that will result in satisfactory damping in roll and reliable lateral control under all flight conditions, while, at the same time, adequate longitudinal control is available.

Note presenting an investigation of the effect of copper oxide in promoting the adherence of vitreous coatings to AISI type 321 stainless steel. It was found that the copper ions in the coating produced a significant increase in adherence on both pickled and sandblasted surfaces but that the effect of the copper decreased with increased firing temperature and increased firing time for the pickled specimens.

"A method is presented for obtaining the attenuation of a shock wave in a shock tube due to the unsteady boundary layer along the shock-tube walls. It is assumed that the boundary layer is thin relative to the tube diameter and induces one-dimensional longitudinal pressure waves whose strength is proportional to the vertical velocity at the edge of the boundary layer. The contributions of the various regions in a shock tube to shock attenuation are indicated" (p. 1).

Note presenting an investigation of the effect of phosphate coatings on the temperature of metal specimens placed in a flame. Small cylindrical specimens of mild steel and S-816 alloy were placed in a natural-gas-air flame at specific temperatures. Special attention is given to the fact that temperature drop was noted in certain specimens and the potential reasons for this reaction are explored.

Note presenting measurements of space heating rate, which can yield information that is useful in characterizing turbulent combustion. For Bunsen burner flames stabilized over a field of pipe-induced turbulence, the space heating rate decreased with increasing linear flow and burner diameter and was independent of pilot conditions. Results regarding residual heat values, space conversion rate, turbulent burning velocities, and a comparison of concepts are provided.

Report presenting an investigation to determine the effect of type and location of impact damage on the fatigue strength of jet-engine compressor blades. The most serious damage was found in the nicks at the leading and trailing edges in the vicinity of the maximum-vibratory-stress section of the airfoil. Results regarding stress distribution in the blades, fatigue of the damaged blades, the fatigue test results, the correlation of reduction in strength, an analysis of the results, and testing using reworked blades are provided.

Report presenting a combination of two previously published reports with an extension of the data to cover properties of fuels up to temperatures as high as 400 degrees Fahrenheit.

Report presenting an investigation of a body-contouring method for alleviating adverse interference of a high-aspect-ratio sweptback wing at high speeds. Modifying the body shape did not significantly affect the aerodynamic characteristics at subcritical speeds, but beneficial results were obtained at free-stream Mach numbers above critical. Results regarding force and pressure studies are provided.

Report presenting a series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge.

Laminar-like and brush-like propane-air flames were obtained when wire grids were used as turbulence generators in a 1/2-inch nozzle burner. The laminar-like flames for grid-disturbed flow had a slightly higher burning velocity than "true" laminar flames (no grid used). The brush-like flames were similar to those obtained with pipe turbulent flow. Their burning-velocity dependence on a "flow disturbance" Reynolds number compared favorably with that obtained for pipe turbulent flames. Hot-wire-anemometer equipment was used to measure the flow disturbance intensity in the cold flow with and without the grids in place.

Report presenting an analysis of temperatures and thermal stresses in typical skin-stiffener combinations of winglike structures subjected to aerodynamic heating using an electronic differential analyzer. Variations were made in aerodynamic heat-transfer parameter, in a joint conductivity parameter, and in the ratio of skin width to skin thickness. Results regarding data obtained,an illustrative example, temperature and stress ratios, and peak stress ratios and temperature-ratio drop across joint are provided.

Report presenting an experimental determination of radiation and recovery corrections and time constraints for several designs of shielded and unshielded thermocouple probes using chromel-alumel wire. Radiation and time constant data were obtained for Mach numbers from 0.3 to 0.9 and a range of static pressures and temperatures. Tables and graphs are presented which show the correction factors of the various designs to aid in selecting a probe for a particular application.

Note presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.

Report presenting a description and comparison of several methods of obtaining the time response of linear systems to either a unit impulse or an arbitrary input from frequency-response data. All of the methods give good accuracy when applied to a second-order system; the main difference is the required computing time.

Report presenting the use of wall perforations on supersonic diffusers to avoid the internal contraction-ratio limitation. Experimental results on a preliminary model of a perforated diffuser at Mach number 1.85 are provided. A theoretical discussion of the flow coefficients and the size and spacing of the perforations are included.

From Summary: "Solutions of mainstream flow patterns for all possible incompressible laminar-boundary-layer flows having classical similarity with respect to rectangular coordinate systems are derived. These solutions, which apply to a wide range of flows, are summarized in table form."

Note presenting a general set of equilibrium differential equations for the plastic buckling of cylinders, which are based on assumptions that have led to the best agreement between theory and test data on inelastic buckling of flat plates. Test data are presented which indicate satisfactory agreement with the theoretical plasticity-reduction factors in most cases. Some of the topics addressed include compressive buckling and torsional buckling.

Report presenting an investigation of a method of casting full-size cermet turbine blades from titanium carbide. An extremely thick piece of titanium carbide was prepared with a small amount of binder, cast into a mold by vibration, centrifuged, and frozen to retain the shape of the mold. Densities and radiographs of the blade prior to infiltration were used as criteria for soundness.

Report presenting a method for obtaining a power spectrum of gust vertical velocity over a wide range of wavelengths from simultaneous measurements in flight. It has the advantage of not involving the use of airplane transfer functions. Results regarding the measurements of velocity, including long-period and short-period measurements, and a composite spectrum over the range of frequencies are provided.