Empirical methods of Ainley and Kochendorfer and Nettles were used to predict performances of nine turbine designs. Measured and predicted performances were compared. Appropriate values of blade-loss parameter were determined for the method of Kochendorfer and Nettles. The measured design-point efficiencies were lower than predicted by as much as 0.09 (Ainley and 0.07 (Kochendorfer and Nettles).

"An investigation was conducted at the NACA Lewis laboratory to determine whether simulated porous gas-turbine blades fabricated by the Eaton Manufacturing Company of Cleveland, Ohio would be satisfactory with respect to coolant flow for application in gas-turbine engines. These blades simulated porous turbine blades by forcing the cooling air onto the blade surface through a large number of chordwise openings or slits between laminations of sheet metal or wire. This type of surface has a finite number of openings, whereas a porous surface has an almost infinite number of smaller openings for the coolant flow" (p. 1).

"Flame speeds based on the outer edge of the shadow cast by the laminar Bunsen cone were determined as functions of composition for methane-air mixtures at initial mixture temperatures ranging from -132 degrees to 342 degrees c and for propane-air and ethylene-air mixtures at initial mixture temperatures ranging from -73 degrees to 344 degrees c. The data showed that maximum flame speed increased with temperature at an increasing rate. The percentage change in flame speed with change in initial temperature for the three fuels followed the decreasing order, methane, propane, and ethylene" (p. 105).

Report presenting a study of rocket-powered models at transonic speeds to determine the effect on the zero-lift drag coefficient of an indented fuselage modification and a thickened wing-root modification of a swept-wing airplane configuration. Results regarding the variation of drag coefficient with Mach number, effect of wing root thickening, and wing-plus-interference drag coefficients for the tested models are provided.

Memorandum presenting results of compressive tests on duplicate longitudinal specimens from sheets of 76S-T6 and R301-T aluminum alloys in three thicknesses as graphs of tangent modulus, secant modulus, and are plotted against stress on a dimensionless basis.

Memorandum presenting an investigation of a 2:1 area-ratio diffuser of length equal to the inlet diameter with several arrangements of simple rectangular vortex generators over a speed range up to an inlet Mach number of 0.5. The investigation was for an inlet boundary layer of 5 percent of the inlet diameter, a condition for which this diffuser had substantial separated areas with no vortex generators. Results regarding the diffuser with no vortex generators, counterrotating vortex generators, other arrangements investigated, and a comparison with results from previous diffuser research are provided.

Report presenting the effect of Mach number on the characteristics of the downwash and wake behind an unswept, tapered wing of aspect ratio 2.67 with full-span, 25-percent-chord, leading- and trailing-edge flaps has been determined from wind-tunnel tests. Results regarding downwash characteristics and wake characteristics are provided.

Memorandum presenting an investigation of the problem of performance losses occurring when airplanes equipped with afterburner and cooling-air ejector installations are flown with the afterburner inoperative. Two sources of the performance losses occurring under some operation conditions were identified: an overexpansion of the propulsive jet and an internal shock system and the excessive pumping action resulting from the off-design.

The forced-convection heat-transfer characteristics of lead-bismuth eutectic were experimentally investigated. Experimental values of Nusselt number for lead-bismuth fell considerably below predicted values. The addition of a wetting agent did not change the heat transfer characteristics.

Report presenting an investigation to determine the control characteristics of flap-type controls of various chords and spans on an unswept wing with a modified double-wedge section, an aspect ratio of 2.5, and a taper ratio of 0.625.The control chords in the study were 25, 35, and 45 percent of the wing chord, and the control spans were 25, 50, and 75 percent of the wing semispan. The data from the study indicated that the control-parameter values are approximately proportional to control chord or span for the chords tested.

Report discussing a pressure-distribution investigation of a wing of a supersonic aircraft in the presence of a fuselage at a specified Mach number and aerodynamic chord. The wing had a quarter chord swept back 40 degrees, an aspect ratio of 4, a taper ratio of 0.5, and 10-percent-thick circular-arc sections perpendicular to the quarter-chord line. The results were compared to a similar investigation at a different Mach number.

Memorandum presenting a review of the current and anticipated lubricant problems as related to aircraft turbojet engines, which has indicated that the current and anticipated bearing operating temperature ranges to be met are specified. The most promising approaches, including types of lubricants and temperatures, are provided.

"Tabulated pressure coefficients and aerodynamic characteristics obtained in flight from pressure distributions over six chordwise rows of orifices on the right wing of the D-558-I research airplane (BuAero No. 37972) are presented. The data were obtained through a Mach number range of 0.80 to 0.89 and throughout the normal-force-coefficient range at Mach numbers of 0.61, 0.70, 0.855, and 0.88. This paper supplements similar tabulated data which have been presented in NACA RM L50J10 and NACA RM L50L12a" (p. 1).

"Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. These data were obtained in an unaccelerated low-speed stall, in push-overs at Mach numbers of approximately 0.83 and 0.99, and in a pull-up at a Mach number of approximately 1.16" (p. 1).

Report presenting an investigation of the aerodynamic problems associated with turbine blades with relatively low solidity and thick profiles, which makes them suitable for use in air-cooled turbines, in a two-dimensional cascade. Testing indicated that supersonic velocities may be obtained over the greater portion of the blade suction surface, resulting in high blade loading without an appreciable decrease in efficiency from that obtained using blades with lower velocities.