Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 to 4.0. Mach number behind the shock, pressure ratio, derivation of flow, and angle of shock are presented on charts. Values are also included for density ratio and change in entropy.

A switching criterion for optimum performance of a third-order contractor acceleration control system having complex roots is presented. Analytical and analog-computer methods are utilized to determine this criterion. The resulting optimum transient responses are presented and compared with those of an equivalent linear system.

From Summary: "Axial fatigue tests at zero mean stress have been made on 0.032- and 0.064-inch 24S-T and 0.032-inch 75S-T sheet-metal specimens 1/4, 1/2, 1, and 2 inches wide without a hole and with central holes giving a range of hole diameter D to specimen width W from 0.01 to 0.95. No systematic difference was noted between the results for the 0.032-inch and the 0.064-inch specimens although the latter seemed the more consistent. In general the fatigue strength based on the minimum section dropped sharply as the ration D/W was increased from zero to about 0.25. The plain specimens showed quite a pronounced decrease in fatigue strength with increasing width. The holed specimens showed only slight and rather inconclusive evidence of this size effect. The fatigue stress-concentration factor was higher for 75S-T than for 24S-T alloy. Evidence was found that a very small hole would not cause any reduction in fatigue strength."

From Introduction: "Experimental results for flow in a rectangular channel with injection through a porous wall are given in reference 1. As part of the study to guide future experiments, laminar flow in a semiporous channel is investigated herein. In the present investigation, a third-order perturbation solution for laminar incompressible flow in a semiporous channel is presented."

"The theory of small disturbances is applied to the calculation of the pressure distribution and drag of a closed body of revolution traveling at supersonic speeds. It is shown that toward the rear of the body the shape of the pressure distribution is similar to that for subsonic flow. For fineness ratios between 10 and 15 the theoretical wave drag is of the same order as probable values of the frictional drag" (p. 1).

Report presenting a comparison of wind-tunnel and flight-measured values of stability and control characteristics. Generally, wind tunnels were found to predict all trends of characteristics reasonably well, but there are differences in parameters for certain values.

Report presenting flight test data obtained from a large swept-wing bomber airplane in flight through rough air at 5,000 feet to determine the effects of vertical translation and pitching motions on the angles of attack of the wing and tail. The results indicate that the motions, particularly the pitching motions, significantly amplify the angles of attack of the wing and tail for the test airplane.

Note presenting heat-transfer rates at the stagnation point of 1.0-inch-diameter glass spherical models in shock-tube flows in air which correspond to free-flight conditions between Mach numbers of 6.4 and 13.9 with stagnation temperatures up to 7900 degrees R. The heat-transfer rates were determined from measurements of the surface-temperature change with time of a thin-film-platinum resistance thermometer.

Note presenting a model with an inverted-V transverse shape and a dead-rise angle of -20 degrees as part of a study of hydrodynamic impact loads on chine-immersed bodies. A series of fixed-trim impacts of the inverted-V model were made in smooth water over a wide range of trim and initial flight-path angles at a beam-loading coefficient of 19.15 with a few impacts at beam-loading coefficients of 27.90 and 36.07. The data are presented in tables and in figures as variations of loads and motions (in coefficient form) with time, trim angle, and flight-path angle.

Report presenting a comparison of two different methods of calculating transient temperatures for thick walls with arbitrary variation of heat-transfer coefficient and adiabatic-wall temperature.

Report presenting three compressor rotors with low-cambered 6-percent-thick NACA 65-series blade sections tested at low speeds. The tests were made at three solidities, without guide vanes or stators, over ranges of blade-setting angles and quantity-flow rates. Results regarding the efficiency and pressure-rise coefficients, variation of section turning angle with angle of attack, comparison between low-speed rotor and cascade turning angles, and carpet pots are provided.

From Summary: "This report describes a theoretical and experimental investigation of the aerodynamic mixing by a standing sound wave downstream from a continuous line source of heat."

Note presenting an investigation at low speed of the performances of circular and annular 90 degree bends of simple shapes conducted for configurations for which the cross-sectional area was constant, expanding, and contracting. Two series of transition bends were included, in which the transition occurred upstream of the bend, within the bend, and downstream from the bend. Results regarding the inlet velocity profiles, exit velocity and total-pressure profiles, and mean total-pressure-loss coefficients and exit total-pressure distortions are provided.

Report presenting a description of a pyrometer that is self-balancing and is able to replace the two conventional manual operations of the line-reversal method. A description of the operation of the pyrometer and the performance and results are provided.

Report presenting linearized-theory calculations of the drag reduction achieved by applying the first three terms of a power series for twist to flat delta wings. For the family of wings investigated, the maximum drag reduction is 2 percent in the medium sweepback range with a steady diminution in both directions. Results for the delta and arrow wings and the optimum settings are provided.

This report summarizes the work that has been carried on in the experimental investigation of the problem of general instability of stiffened metal cylinders subjected to pure bending at the C.I.T. This part of the investigation included tests of 46 sheet-covered specimens. The most significant result was the determination of a new design parameter for the case of a stiffened metal cylinder subjected to pure bending.

Report presenting the results of an experimental and theoretical investigation of the vaporization of fuel droplets in heated air under atmospheric pressure. An experimental investigation of the temperature and mass histories of single droplets was made, a comparison of the experimental results was conducted with calculated temperature and mass histories, and the time taken by a droplet vaporizing to for a mixture of fuel vapor and air of combustible strength is calculated.

Report presenting analytical solutions for the temperature and thermal-stress distributions in thick skins and structural elements such as angle, channel, T-, and H-sections when heated at a constant rate.

Note presenting wind-tunnel calibrations of three types of angle-of-attack sensing devices - the pivoted vane, the differential pressure tube, and the null-seeking pressure tube. Flight data on the position errors for three sensor locations - ahead of the fuselage nose, ahead of the wing tip, and on the forebody of the fuselage - are also presented. Various methods for calibrating angle-of-attack installations in flight are briefly described.

Report presenting an investigation in the 7- by 10-foot tunnel by means of the transonic-bump technique to determine the lift augmentation of several jet-flap configurations. The investigation covered a range of Mach numbers. The results indicated that the lift can be increased at any Mach number by blowing downward through a number of closely spaced holes along and near the trailing edge of the wing.

Note presenting the effect of temperature on Young's modulus of elasticity as determined for 2024-T3 and 7075-T6 aluminum alloys, AZ31A-0 magnesium alloy, RS-120 titanium alloy, and type 303 stainless steel by flexural vibration tests of beam specimens at temperatures from room temperature to 900 degrees Fahrenheit. The test frequencies were varied from 40 to 550 cycles per second.

Note presenting a study of aluminum alloy containing 4 weight percent copper during aging using low-frequency internal-friction measurements in torsional and flexural vibration. Both polycrystalline and single-crystal specimens exhibit an initial internal-friction peak at 173 degrees Celsius after solution treatment and quenching.

Report presenting an investigation at low speed to determine the Magnus effect on various sections of a body of revolution of which several sections could be rotated either as individual units or in combinations. The investigation included the measurement of the Magnus effect on the body alone and on the body with a three-blade propeller.

Report presenting an approximate analysis of the nonlinear effects of initial twist and large deflections on the torsional stiffness of a cantilever plate subjected to a nonuniform temperature distribution. The results show that the initial twist and applied moments can have significant effects on the changes in stiffness produced by nonuniform heating. Results regarding the general results of equations and comparison with experiment are provided.