Memorandum presenting a two-dimensional wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and difficulties encountered in obtaining extensive laminar flow are provided.

Memorandum presenting the boundary-layer velocity profiles were measured on ten samples of various porous materials and on impervious aluminum plate mounted flush with the inner surface of the side wall of a small wind tunnel. Suction was applied to the back side of the porous test materials through a 4-inch-square opening. Results regarding measurements on the impervious plate and measurements on porous materials without suction and with suction are provided.

"An investigation of forced-convection heat transfer and associated pressure drops was conducted with air flowing through electrically heated Inconel tubes having various degrees of square-thread-type roughness, an inside diameter of 1/2 inch, and a length of 24 inches were obtained for tubes having conventional roughness ratios (height of thread/radius of tube) of 0 (smooth tube), 0.016, 0.025, and 0.037 over ranges of bulk Reynolds numbers up to 350,000, average inside-tube-wall temperatures up to 1950deg R, and heat-flux densities up to 115,000 Btu per hour per square foot" (p. 1).

Memorandum presenting a supplementary investigation in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement on the spin and spin-recovery characteristics of a scale model of the McDonnell F2H-3 airplane. Results regarding wing-tip tanks and experimental aerodynamic shapes are provided.

Memorandum presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation relates the average combustion-chamber wall temperature at a station near the combustion-chamber outlet to the temperatures of the cooling air and combustion gas, and to the mass flows of the cooling air and combustion gas.

Report presenting an investigation of the effects of a variation of Reynolds number on the forces, moments, and surface pressures on a semispan model of a wing with 35 degrees of sweepback, an aspect ratio of 5, a taper ratio of 0.7, and the NACA 65(sub 1)A012 section in planes parallel to the plane of symmetry.

Report presenting the design and performance of a turbine to drive a supersonic compressor in order to determine the problems that would be encountered in turbines required to drive high-speed, high-weight-flow compressors. A model of the turbine was built and operated over a range of speed and total-pressure ratios. Results regarding performance, the effects of rotor choking, and possible modifications to the design are provided.

Report presenting the results of an investigation to determine the effect of chord discontinuities and chordwise fences on the static longitudinal stability and wake characteristics of an airplane model with a 35-degree sweptback wing. The use of a fence or chord extension was found to cause a slight improvement in the static longitudinal stability of the basic wing alone. The force data and flow characteristics in the form of wake surveys and surface tufts are provided.

From Summary: "An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.93 to determine the effects on the chordwise pressure distributions of projecting various spoiler-type ailerons on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6. The results of the investigation are presented as curves of chordwise pressure distributions near the midspan of the spoilers (0.46-wing-semispan station)."

Report presenting the results of a free-flight investigation to determine the drag of circular, finite-length cylinders for a range of Mach numbers. For supersonic speeds, the drag of circular cylinders was found to be largely independent of fineness ratio and Reynolds number.

Report presenting a wind-tunnel investigation of two full-span and two semispan models with 45 degrees of sweepback, an aspect ratio of 5.5, and a taper ratio of 0.53. The lift and drag data obtained from tests of the semispan agreed well with data obtained on the full-span model. Results regarding a comparison of the data for the full-span and semispan models, full-span model data, and effect of surface roughness are provided.

From Introduction: "The purpose of this report is to compare the effect on engine performance of the variable-area exhaust nozzle for axial- and centrifugal-flow turbojet engines."

Report presenting an investigation of an air-cooled internal-strut-supported blade in a modified production turbojet engine to determine the cooling effectiveness of this type of blade and the cooling-air pressure loss through the blade under engine operating conditions. Experimental results are presented and compared with the results of an analytical investigation.

Memorandum presenting an investigation to determine the practicability of using blade boundary-layer control in order to obtain high turning angles in a stator-blade row. The overall performance of the stage was obtained for a range of weight flows at each of three tip speeds with and without hub section. Results regarding slot configuration, overall performance, and stator-blade wakes are provided.

Report presenting tests to evaluate the usefulness of available theory for the calculation of lift-curve slope and center of pressure of low-aspect-ratio, triangular, and rectangular cruciform wings in combination with a long slender body. Tests were made over a range of Mach and Reynolds numbers based on model length.

Report presenting investigations of the effects of fuel properties on combustion-chamber carbon deposition in singe tubular fuel-atomizing and fuel-prevaporizing combustors. The NACA K factor and the smoking tendency were approximately equally effective in relating carbon-deposition data from the prevaporizing and atomizing combustors. Results regarding the K factor, smoking tendency, effect of prevaporizing combustor operating conditions, sulfur, gum, and olefin, are provided.

Report presenting an investigation of internal film cooling of the exhaust nozzle of a 1000-pound-thrust liquid ammonia liquid-oxygen rocket engine. With water as a coolant, approximately 16 percent of the total propellant and coolant flow was required to film-cool the entire nozzle and with anhydrous liquid ammonia, approximately 19 percent of the total flow was required. Results regarding the coolant results and performance results are provided.

Report presenting a flight investigation using rocket-powered models to determine some of the effects of wing-to-tail distance on the stability and control characteristics of a canard-missile configuration with 60 degree delta wings and control surfaces. Both models were tested over a range of Mach numbers from 0.8 to 2.0, and canard hinge moment and model drag data are presented. Testing indicated that additional fuselage length increases the lift-curve slope slightly and has very little effect on minimum drag.

"Supplementary blade-design data including rotor- and stator-blade coordinates and mean-line angles at the leading and the trailing edges are presented for a transonic axial-flow compressor inlet stage" (p. 1).

Report presenting pressure distributions, tuft patterns, and schileren surveys of a sweptback wing-fuselage combination in the 8-foot transonic tunnel at a range of Mach numbers and angles of attack. The wing had 45 degrees of sweepback, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Results regarding an angle of attack of 0 degrees, 4 degrees, 6 degrees, 8 degrees, 12 degrees, and 20 degrees are provided.

Memorandum presenting a measurement of the mean skin-friction coefficients on a flat-plate model, with and without initial roughness, and on a wind tunnel wall were measured at a nominal Mach number of 5.5 over a range of Reynolds numbers.

From Introduction: "The present report is intended to give a qualitative picture of the operation of each stage of a multistage compressor over a range of actual operating conditions from 50 to 100 percent design speed and to point out some means of achieving improved off-design performance. The method used in the report is primarily analytical and is based on single-stage-performance results."

Report presenting pressure and temperature changes in the cooling air flowing through air-cooled gas-turbine blades, which have been measured experimentally in a static cascade on a 10-tube blade for isothermal and nonisothermal flows, and on a 13-fine blade for isothermal flows. Values of pressure and temperature were obtained for a range of cooling-air flows over a range of Reynolds numbers, Mach numbers, and heat-transfer rates.

Memorandum presenting a study made to ascertain some of the operational characteristics of four types of air-induction systems for a turbojet-powered airplane intended to operate at a range of Mach numbers at an altitude of 35,332 feet. The investigation included air-induction systems with and wthout ramps to produce oblique shock waves, with fixed and variable inlet areas, and with divergent diffusers.