Describes the characteristics of the Russian-olive and the benefits of growing it.

Describes the characteristics of red-headed pine sawflies, the damage they cause to varieties of pine trees, and methods of control.

Memorandum presenting an analysis made to estimate the performance of a direct-air nuclear turbojet-powered airplane using a split-flow reactor and a separated-type shield. The analysis was for flight Mach numbers of 0.9 and 1.5 and covered a range of altitudes, reactor-wall temperatures, turbine-inlet temperatures, compressor pressure ratios, and airplane lift-drag ratios.

Note presenting comparisons of the low-speed experimental lift and hinge-moment parameters of flapped lifting surfaces with and without sweepback with values computed by several theoretical procedures. Based on these limited results, one theoretical method appears to be more satisfactory than the other methods investigated and is therefore recommended fore preliminary design estimates. Sample calculations are included.

"The sandwich plate consisting of corrugated sheet fastened between two face sheets is considered. Application of existing theories to the analysis of such a sandwich plate requires the knowledge of certain elastic constants. Formulas and charts are presented for the evaluation of these constants" (p. 1).

Note presenting the lift-due-to-pitching derivative and the damping-in-pitch derivative, which were derived for a series of thin sweptback tapered wings with streamwise tips and subsonic leading edges. The effects of camber and thickness were not considered.

Note presenting static and fatigue tests made on several types of joints in 75S-T6, 24S-T4, and 14S-T6 high-strength aluminum-alloy extruded bar. In the static tensile tests, the 75S-T6 double-shear joint withstood the highest ultimate load, 115,250 pounds, and the 75S-T6 clamped-keyed joint the lowest, 55,000 pounds, a ratio of 2.08 to 1.

Report presenting an investigation in Langley tank no. 1 to determine the effects of increasing the angle of dead rise on various hydrodynamic qualities of a flying-boat hull with a length-beam ratio of 15. Results regarding the longitudinal stability, spray characteristics, take-off performance, rough-water landing characteristics, and a summary chart are provided.

The longitudinal stability and control characteristics of a B-29 airplane have been measured with a control surface booster incorporated in the elevator-control system. The measurements were obtained with the booster operating to provide various control-force gradients and various maximum rates of control motion. Results are presented which show the effect of these booster parameters on the handling qualities of the test airplane.

"Tests of two propellers having two blades and differing only in the inboard pitch distribution were made in the Langley 8-foot highspeed tunnel to determine the effect of inboard pitch distribution on propeller performance. Propeller was designed for operation in the reduced velocity region ahead of an NACA cowling; the inboard pitch distribution of the modified propeller was increased for operation at or near free-stream velocities, such as would be obtained in a pusher installation. Conditions covering climb, cruise, and high-speed operation" (p. 1).

Report presenting a review of turbulent-boundary-layer analyses and experimental data for average skin-friction coefficients on a flat plate in high-speed flow. New solutions are presented which show the effect of using a continuous velocity gradient and the effect of the extent of the laminar sublayer on the average skin-friction coefficient.

Report presenting an investigation of 16-inch-diameter ram-jet units under free-flight conditions to determine performance at high subsonic, transonic, and supersonic velocities. Full-scale units were released from the airplane at high altitudes and accelerated by the engine thrust and force of gravity. Results regarding the diffuser total-pressure recovery, drag, thrust coefficient, and combustion are provided.

Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, which has been twisted and cambered for a trapezoidal span load distribution at subsonic and supersonic Mach numbers.

Report presenting an investigation in the supersonic tunnel at Mach number 1.85 and angles of attack from 0 to 5 degrees to determine optimum design configurations for a convergent-divergent type of supersonic diffusers with a subsonic diffuser of 5 degrees included divergence angle. Total-pressure recoveries in excess of the theoretical recovery across a normal shock at a free-stream Mach number of 1.85 were obtained with a number of configurations.

Report discusses the results of aerodynamic testing of an unswept, tapered wing with full-span, 25-percent-chord, plain, leading- and trailing-edge flaps at several angles of attack, leading-edge-flap deflection, and trailing-edge-flap deflection. This testing was done in an attempt to reduce the lift coefficients of the wings at moderate angles of attack and to provide more control for flight in the transonic Mach number range.

Report presenting aerodynamic characteristics of an unswept wing with an aspect ratio of 2.67, a taper ratio of 0.5, and employing full-span, 25-percent chord, plain, leading-edge flaps using wind-tunnel testing of a semispan model. The leading edge flap was generally effective at changing both the lift and pitching-moment coefficients at each angle of attack and Mach number. Results regarding lift characteristics, hinge-moment characteristics, drag characteristics, and pitching-moment characteristics are provided.

From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of reference 1."

Report presenting the results of a series of exploratory flights on a 35 degree swept-wing airplane up to Mach number 1.09 to show the effects of compressibility on imposing maneuverability limits. Results regarding the maneuvering accelerations and buffet boundary are provided.

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 an investigation of the effects of three centrally mounted wing-tip tanks on the aerodynamic characteristics of a cambered wing with an aspect ratio of 10 and 35 degrees of sweepback. Testing occurred over a range of Mach and Reynolds numbers and lift, drag, and pitching-moment were measured.

An investigation was made of the spray characteristics of a jet-powered dynamic model of the Bureau of Aeronautics DR 56 flying-boat design with a vee tail. A limited investigation was made to determine the effect of the change in tail design on the take-off and landing behavior in smooth water and in waves 8 feet high (full size).

Memorandum presenting the effects of specimen-axis orientation with respect to forging direction on the true stress-strain curves and the fracturing characteristics at room temperature of forged and subsequently heat-treated billets of alloys 16-25-6, S-816, and Inconel X. Results regarding plastic properties and fracture properties are provided.

Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0008-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.

Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0005-63 sections in streamwise planes has been investigated at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.