From Summary: "The results of a computational program are presented which give numerical values of the stiffnesses required of the various components of a multipost-stiffened wing to achieve desired buckling-stress values under bending loads. Two arrangements of the posts are considered, upright posts and posts used as diagonals of a Warren truss. This work extends and summarizes the calculations presented in NACA RM L52K10a."

Note presenting the operating characteristics of an acceleration restrictor which limits the normal acceleration of an airplane in maneuvers determined from tests on a simulator. The simulator consisted of a control stick geared to a magnetic brake unit and an analog computer which simulated the dynamic characteristics of the airplane.

Report presenting the two-dimensional aerodynamic characteristics of an NACA 64A010 airfoil with a slat at a range of Mach numbers. Two types of slat positions were investigated, one with the slat leading edge extended forward along the airfoil chord line and one with the slat extended forward and displaced below the chord line. Results regarding lift, drag, pitching moment, and pressure distribution are provided.

Report presenting experiments to study the start of fretting and cause of damage during the early stages of fretting of steel-steel combinations at a frequency 5 cycles per minute, an amplitude of 0.006 inch, a load of 150 grams, in air with relative humidity of less than 10 percent. Pure iron, glass, and iron oxide powder compacts were used in supplementary experiments.

From Summary: "Linearized compressible-flow analysis is applied to the study of wind-tunnel-wall interference for subsonic flow in either two-dimensional or circular test sections having slotted or porous walls. Expressions are developed for evaluating blockage and lift interference."

Note presenting tests conducted to determine the factors influencing the thermal conductance across the interference between 75S-T6 aluminum-alloy and AISI Type 416 stainless-steel structural joints. The type of joints investigated included: bare metal-to-metal contact, contact surfaces coated with zinc-chromate primer, contact surfaces separated by thin foils of good conductors, contact surfaces separated by thin sheets of insulation, contact surfaces joined by strength-giving bonds, and riveted joints. The factors investigated were heat flow, temperature drop, temperature level, and surface condition.

Note presenting structural analyses made for four straight multicell wings. Wings with aspect ratios of 2 and 4 with rectangular and biconvex cross sections have been considered. The results indicated that under bending loads, all of the wings show fairly good agreement with beam theory.

Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord.

Report presenting wind-tunnel tests of a body of revolution with a circular nose inlet conducted at low speeds to ascertain some of the effects of inlet lip bluntness and profile on diffuser performance and body drag. Testing occurred at free-stream Mach numbers up to 0.330 with inlet flows from zero to choking and a steady 0 degree angle of attack and angle of yaw. Results regarding the internal-flow studies with the strut-mounted model and drag and surface-pressure studies with the sting-supported model are provided.

Note presenting pressure-distribution expressions and stability derivatives derived by use of linear theory for zero-end-plate triangular vertical tails with subsonic leading edges performing rolling, yawing, and constant-lateral-acceleration motions. Corresponding results for the sideslip motion, most of which have been previously reported, are also included.

Report presenting a simple method of experimentally determining the product of inertia and the inclination of the principal longitudinal axis of inertia of an airplane. The results of the method are provided and a description of the equipment and techniques are given for a simple model and a conventional airplane. Results regarding moments of inertia about the body reference area, the product of inertia and inclination of the principal axis, and the principal moments of inertia are provided.

Report presenting turbulent-heat-transfer measurements obtained through the use of a three-dimensional axially symmetric annual nozzle consisting of an inner shaped plug and an outer cylindrical sleeve at Mach number 3.03. Results regarding the variation of wall temperature with longitudinal distance, variation of local Nusselt number with local Reynolds number, and variation of local temperature-recovery factor with local Reynolds number are provided.

Report presenting temperatures on the external surface of a straight hollow cylinder aligned parallel to the air stream. Results regarding the recovery-factor distribution without roughness, transition without roughness, transition caused by roughness, and analysis of roughness results are provided.

"The lift, drag, and pitching-moment characteristics of the AGARD Calibration Model B as determined in the Langley 9-inch supersonic tunnel are presented at Mach numbers of 1.62, 1.94, and 2.41 and at a Reynolds number, based on body length, of approximately 3.0 x 10(exp 6). The zero-lift drag data compared favorably with available data and were in the proper sequence for the effects of Reynolds number" (p. 1).

From Summary: "The maximum loads of idealized inelastic H-section columns whose pinned ends approach each other at a constant rate are presented. The solutions indicate that as the rate of end displacement becomes smaller, the dynamic buckling solutions approach the static solution as a lower limit. The effects of inertia forces are apparently negligible at rates of end displacement comparable to those normally used in static column tests."

From Summary: "The presence of radomes and instruments that are sensitive to water films or ice formations in the nose section of all-weather aircraft and missiles necessitates a knowledge of the droplet impingement characteristics of bodies of revolution. Because it is possible to approximate many of these bodies with an ellipsoid of revolution, droplet trajectories about an ellipsoid of revolution with a fineness ratio of 10 were computed for incompressible axisymmetric air flow. From the computed droplet trajectories, the following impingement characteristics of the ellipsoid surface were obtained and are presented in terms of dimensionless parameters: (1) total rate of water impingement, (2) extent of droplet impingement zone, and (3) local rate of water impingement."

The trajectories of droplets in the air flowing past an NACA 65AO04 airfoil at an angle of attack of 8 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. These impingement characteristics are compared briefly with those previously reported for the same airfoil at an angle of attack of 4 deg.

From Summary: "Effects of local panel oscillations on bending and torsional vibrations of box beams with flexible covers and webs are investigated. Theoretical analyses of simplified models are made in order to shed light on the mechanism of coupling between local and overall vibrations and to derive results than can be used to estimate the coupling effects in box beams."

From Introduction: "These aerodynamic data were used previously in an analytical investigation of a spin recovery by rudder reversal, the results of which have been published in reference 2. Because of certain discrepancies in the rotary-balance data similar to those discussed in reference 3, some modifications were made to the aerodynamic data used in calculating the results in reference 2 and also the results in this paper; these discrepancies and modifications are discussed in detail herein."

Report presenting an investigation of a 1/19-scale model of an unswept-wing trainer airplane in the 20-foot free-spinning tunnel to determine the rocket spin-recovery characteristics of the model for comparison with available full-scale-airplane results. A rocket was attached to each wing tip to fire in a direction to apply an antispin yawing moment about the Z body axis. Results regarding the full-scale spin recoveries by rockets, model spin recoveries by rudder reversal, model spin recoveries by rockets, and mass changes associated with installation of emergency device are provided.

"The analogy between a ball rolling over a contoured surface and a pitching and yawing aircraft is developed. Test results from a model representing a missile with linear moment characteristics are presented to verify the analogy. Several examples of the behavior of nonlinear systems are also given" (p. 1).

Report presenting the total zero-lift drag of a fin-stabilized parabolic body of revolution designated the RM-10 using scale models launched from a gun through still air at a range of Mach and Reynolds numbers. Results indicated that the location of transition had an important effect on the drag of the configuration.

Report presenting the static properties and resistance characteristics of a family of seaplane hulls with a variety of length-beam ratios. The hydrodynamic stability and rough-water behavior of the family of hulls has been reported on previously. Results regarding static properties, resistance characteristics, and take-off calculations are provided.

Report presenting experiments that have been conducted to determine average skin-friction coefficients in the absence of heat transfer for completely turbulent flow along the cylindrical portion of cone-cylinder bodies of revolution with several overall fineness ratios. Numerous boundary-layer surveys were made to enable all data to be based on an effective starting position of the turbulent flow. Results regarding tripping devices to insure turbulent flow, effect of nose shape, attainment of equilibrium in the blowdown tunnel, a comparison of data from wind tunnels, effect of pressure gradient, and skin friction values using several different configurations are provided.