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.

Report presenting an investigation of large-chord flap-type controls with sweptback hinge lines and with various sizes and shapes of horn balances on a triangular wing of aspect ratio 2. Changes in the following elements were investigated: shielding of the horn balance, percentage of horn balance, trailing-edge thickness, flap nose seal, contour of the horn balance, and Reynolds number.

Report presenting an investigation in the high-speed wind tunnel to determine the aerodynamic characteristics of three triangular wings and a trapezoidal wing through the transonic speed range by use of the bump technique. Data was obtained over a range of Mach and Reynolds numbers. Results regarding the lift, drag, pitching moment, and lift-drag ratio of the various wings are provided.

Report presenting testing on the NACA 16-009 airfoil and on eight airfoils of the NACA 6A series, which shows that the chordwise loading due to lift at a Mach number of 1.0 is insignificantly affected by thickness distribution within the range of airfoil shapes presented and only slightly affected by thickness. Results regarding the experimental loading on symmetrical airfoils, method of estimating pressure distribution, experimental loadings on cambered airfoils, and scope of method are provided.

Memorandum presenting an investigation conducted to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a cambered and twisted wing with an aspect ratio of 3.0 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for specified Mach and Reynolds numbers. In order to determine the effects of camber and twist, the force, moment, and pressure data are compared with the data for an uncambered and untwisted wing of the same plan form.

Report presenting a method based on geometric factors of the coolant passage was evolved for the rapid selection and evaluation of coolant passage configurations for air-cooled turbine rotor blades. The most promising coolant passage configurations are analyzed to obtain absolute values of the required cooling-air weight flow, pressure loss, and strength characteristics.

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.

Report presenting an investigation of a series of wings of various plan forms in the high-velocity field of the side-wall reflection plate of the 7- by 10-foot tunnel at a range of angles of attack and Mach numbers. The results indicated that the maximum lift coefficients obtainable increased with increase in sweep angle and decreased with Mach number at the lower subsonic Mach numbers.

Report presenting an investigation of the stage work distribution and losses through the turbine at design conditions of the XJ35-A-23 two-stage turbine. The investigation showed that the poor performance was primarily due to large whirl velocities at the turbine exit, choking in the second-stage rotor, and a choking condition upstream of the physical blade throat. If these conditions are eliminated, satisfactory two-stage turbine performance can be obtained.

Report presenting testing of a parabolic body of revolution in the 4- by 4-foot supersonic tunnel at two Mach numbers. The investigation included the effects of Reynolds number, fins, internal contour of body base, and two support systems on body pressure and force drag at an angle of attack of 0 degrees.

Report presenting the performance characteristics of a turbine with nontwisted rotor blades suitable for air cooling. Results regarding overall performance and flow surveys at the stator and rotor exits are provided.

Report presenting the longitudinal frequency-response characteristics and the stability derivatives of the Douglas D-558-II airplane at a range of Mach numbers and altitudes. Results of experimentation were compared to computed values.

Report presenting an investigation of a nacelle in three chordwise locations at each of four spanwise locations in an underwing position on a small-size semi-span model of a wing sweptback 45 degrees and tapered in thickness from 9 percent at the root to 3 percent at the tip. Results regarding drag characteristics, lift-drag ratios, lift characteristics, pitching moment characteristics, and lateral center of pressure are provided.

Memorandum presenting a review of the acceleration characteristics of an axial-flow turbojet engine with a fixed-area exhaust nozzle as obtained from transients induced by large steps in fuel flow under sea-level static conditions. Maximum acceleration and thrust appeared obtainable through the use of a proposed fuel schedule that required only small initial steps in fuel flow. Results regarding linearity, maximum acceleration and thrust, and fuel-flow schedule are provided.

Report presenting testing of two ceramals for use as gas-turbine blade materials. Results regarding the tensile strength, modulus of rupture, thermal shock, and turbine-blade evaluation are provided.

A brief summary is made of the performance of a series of variable-geometry type scoop inlets investigated at the Lewis Laboratory on a model of the X-3 airplane fuselage. Data are presented for a range of inlet mass-flow ratios over a Mach number range from 0 to 2 and from 0 degrees to 12 degrees angle of attack. Rounded-lip inlets are found to give satisfactory performance to a Mach number of 1.5. Use of sharp rather than blunt lip configurations is shown to provide considerable gains in available thrust at Mach number 2.0 but penalize take-off performance to the extent that auxiliary air intakes may be required.

Report presenting a low-speed wind-tunnel investigation to determine the static lateral control characteristics of flap-type spoiler ailerons on a thin delta wing equipped with a double slotted flap. A spoiler located on the flap gave rolling-moment coefficients that varied fairly linearly with spoiler projects and with about the same magnitude for either the flap-retracted or flap-deflected position.

From Summary: "An investigation was conducted at simulated high-altitude flight conditions to evaluate the use of compressor evaporative cooling as a means of turbojet-engine thrust augmentation. Comparison of the performance of the engine with water-alcohol injection at the compressor inlet, at the sixth stage of the compressor, and at the sixth and ninth stages was made. From consideration of the thrust increases achieved, the interstage injection of the coolant was considered more desirable preferred over the combined sixth- and ninth-stage injection because of its relative simplicity."

Report presenting an investigation of the physical properties of slurries and the use of a metal-soap additive to prepare stable slurries of commercial magnesium, aluminum, and boron powders in a MIL-F-5624 grade JP-3 base fuel. Results regarding the slurry density, apparent viscosity, apparent surface tension, stability, and fuel-flow characteristics are provided.

At the request of the Bureau of Aeronautics, Department of the Navy, an investigation at transonic and low supersonic speeds of the drag and longitudinal trim characteristics of the Douglas XF4D-1 airplane is being conducted by the Langley Pilotless Aircraft Research Division. The Douglas XF4D-1 is a jet-propelled, low-aspect-ratio, swept-wing, tailless, interceptor-type airplane designed to fly at low supersonic speeds. As a part of this investigation, flight tests were made using rocket- propelled 1/10- scale models to determine the effect of the addition of 10 external stores and rocket packets on the drag at low lift coefficients. In addition to these data, some qualitative values of the directional stability parameter C(sub n beta) and duct total-pressure recovery are also presented.

"An investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds was conducted at the NACA Lewis altitude wind tunnel. This report evaluates the compressor modifications which were restricted to (1) twisting rotor blades (in place) to change blade section angles and (2) inserting new stator diaphragms with different blade angles. Such configuration changes could be incorporated quickly and easily in existing engines at overhaul depots" (p. 1).