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."

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."

Report presenting a linearized theoretical analysis made to determine minimum-wave-drag airfoil sections for arrow wings having the same airfoil sections at all spanwise sections. Numerical computations of the airfoil shape and wing wave drag were performed for a delta wing and an arrow wing with a ratio of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle of 0.4.

Note describing the preparation and evaluation of 25 binary and ternary alloys with liquidus temperatures in the range of 2000 to 2500 degrees Fahrenheit as part of an investigation of potential brazing alloys for molybdenum for use at elevated temperatures. Three commercial alloys were also investigated.

Report presenting a method for determining the lateral-stability derivatives, transfer-function coefficients, and the modes for lateral motion from frequency-response data for a rigid aircraft. The method is based on the application of the vector technique to the equations of lateral motion, so that the three equations of lateral motion can be separated into six equations. Two numerical examples are given to demonstrate the use of the method.

Report presenting an investigation of fuel injection into a combustion chamber, including theoretical and experimental results regarding the unsteady-state portion of the total vaporization time of single fuel droplets injected into air.

Report presenting a theoretical investigation of the contribution of horizontal tails to the lift and pitching moment due to angle of attack, a constant rate of pitch, and a constant vertical acceleration. Methods for calculating the flow fields behind wings with constant vertical acceleration are developed.

Report presenting the linearized drag integral for bodies of revolution at supersonic speeds in a double-integral form which is not based on slender-body approximations but which reduces to the usual slender-body expression in the proper limit. The minimum-external-wave-drag problem is solved for a transition section connecting to two semi-infinite cylinders.

Note presenting the results of buckling tests of long square tubes loaded in compression, torsion, and combined compression and torsion and a comparison with theoretical compression and shear buckling curves and with theoretical interaction curves for the buckling of simply supported flat plates. Results regarding the pure compression and pure torsion buckling and combined compression and torsion buckling are provided.

Report presenting experiments conducted as part of the general rocket-research program to determine the heat-transfer and fluid-friction characteristics of white fuming nitric acid over a specific set of conditions.

Report presenting an evaluation of an aircraft radio altimeter for use in a method of airspeed calibration differing from the radar-photothedolite method of a previous study only in that the geometric altitude is obtained from an aircraft radio altimeter. The accuracy and airspeed calibrations for the two methods were found to be similar.

Report presenting an experimental investigation to define the downwash field and vortex-sheet shape behind a large-scale wing-fuselage combination with a 63 degree sweptback wing of aspect ratio 3.5. At positive angles of attack, the vortex sheet assumed a shape which initially bowed upward but flatten out downstream before the rolling-up process had occurred to an appreciable degree. Results regarding downwash data, shape and location of the vortex sheet, path of the vortex core, and comparison of theories with experimental results are provided.

Note presenting an investigation of the importance of triple collisions in the thermal relaxation process of gaseous mixtures. Results of the experiments have shown that the thermal relaxation times of the gas mixtures studied can be very well explained on the basis of binary collisions alone and that triple collisions do not play a discernible part in the excitation of molecular vibrations.

Report presenting a low-speed investigation in the stability tunnel to determine and improve, if possible, the directional stability characteristics of two tandem helicopter fuselages, one representing a helicopter with overlapping rotors and the other a helicopter with nonoverlapping rotors. Results regarding the presentation of data, directional stability of overlap-type fuselage, and directional stability of nonoverlap-type fuselage are provided.

Note presenting tables and figures of a standard atmosphere based on the Manual of the ICAO Standard Atmosphere. Detailed tables of pressures and densities are given for altitudes up to 20,000 meters and to 65,000 feet.