Describes the U.S. federal grades given to determine product quality, and how these grades are used for butter.

Describes methods of growing buckwheat, and ways to use the crop.

Report regarding the ongoing development of both multi-alkali photocathodes and improved photomultipliers.

Memorandum presenting an investigation of three models of a delta-wing airplane designed for a long-range subsonic cruise and a supersonic dash. Results regarding the aerodynamic characteristics of the models and effect of elevon deflection on aerodynamic characteristics of the four-engine model are provided.

Memorandum presenting three types of aerodynamic interference originating from forward components of airplanes, which are shown to contribute to decreased vertical-tail effectiveness. The vorticity originating from a slender fuselage ahead of the wing resulted in a marked reduction in vertical-tail effectiveness with angle of attack for one model.

"Trajectories of water droplets moving in the ideal two-dimensional flow field ahead of a body of rectangular cross section and infinite extent in the downstream direction have been calculated by means of a differential analyzer. Data on collection efficiency and distribution of water impingement are presented" (p. 1).

Report discussing an evaluation of a series of half-conical side inlets mounted on the fuselage of a supersonic aircraft at various Mach numbers. Information about the maximum total-pressure recovery, asymmetrical operation of the twin-duct system, potential reduction in stable mass-flow range, boundary-layer diverter height, and engine mass flow is described.

Memorandum presenting a supersonic wind-tunnel investigation of store interference performed in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 in which separate forces on a store and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with a large external store.

Memorandum presenting an investigation in the blowdown tunnel of the pressure tunnel to determine the aerodynamic characteristics of a sting-mounted Douglas Aircraft Company store in the presence of, but not attached to, an unswept semispan cantilevered wing of aspect ratio 4.0. The influence of the store on the aerodynamic characteristics of the wing was also obtained.

Jet engine induction systems investigations and relationship of air inlets, drag, airframe, pressure recovery, flow and interferences.

Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner. A 70-percentage-point reduction in combustion efficiency resulted when the combustion-chamber length was reduced from 62 to 10 inches.

Memorandum presenting a wind-tunnel investigation in which dynamic models that included elastic simulation were used to study the flight characteristics of a swept-wing bomber with parasite swept-wing fighters coupled at the wing tips. The configuration is meant to represent an efficient towing arrangement whereby the operational range of fighters can be increased.

Report discussing the use of radioisotope tracer techniques to study the following phenomena: the effect of nickel dip on the deposition of cobalt metal during firing of a cobalt-bearing ground coat, the effect of surface pretreatment on the amount and distribution of nickel deposited from nickel dip on enameling iron, and the effect of application and firing of cobalt-free and cobalt-bearing enamels on the chemical form and physical distribution of nickel previously deposited on enameling iron by the nickel dip.

Note presenting experimental modes and frequencies of a uniform built-up box beam and comparisons between experimental and theoretical frequencies. 14 natural beam frequencies obtained from vibration tests of a built-up box beam are presented.

Report presenting an analysis of approximately 70,000 hours of V-G data from one type of two-engine transport airplane to determine the severity and frequency of occurrence of the gust loads and gusts. The data were obtained during routine feeder-line and short-haul commercial operations in six different routes over the course of eight years. Results regarding the distribution of acceleration, gust velocity, and airspeed, confidence bends, and acceleration and gust velocity envelopes are provided.

"Studies of various arrangements of wings and bodies designed to provide favorable wave interference at supersonic speeds lead to the problem of determining the minimum possible valve of the wave resistance obtainable by any disposition of the elements of an aircraft within a definitely prescribed region. Under the assumptions that the total lift and the total volume of the aircraft are given, conditions that must be satisfied if the drag is to be a minimum are found. The report concludes with a discussion of recent developments of the theory which lead to an improved understanding of the drag associated with the production of lift" (p. 1).

Report presenting an experimental investigation to determine the scale effects of the forces from water spray generated by a flat rectangular planing surface and impinging on a collector plate representative of an aerodynamic surface or other part of a water-based airplane. Lift and drag forces on the flat rectangular planing surface and the spray-collector plate were measured.

Report presenting measurements of lift, drag, and pitching moment of an NACA 0011 airfoil in icing using two types of pneumatic de-icers, one with spanwise inflatable tubes and the other with chordwise tubes. Results regarding the airfoil characteristics with the de-icer operating and effect of primary ice formation on drag, lift, and pitch with the de-icer inoperative are provided.

Note presenting an evaluation of the integrals which occur in the aerodynamic theory for wings oscillating in pure supersonic flow for various Mach numbers and values of the reduced frequency.

Report presenting a method in which the contact vertical velocities of airplanes are obtained on a statistical basis from measurements of maximum incremental center-of-gravity acceleration. 268 landings with a small trainer airplane using this method have been made. Data regarding calibration curves, some results obtained during landings of a large flexible airplane, and the possibility of using only analytical methods for calibration are provided.

Report presenting a statistical analysis of vertical velocities at second wheel to touch made from photographs of 353 landings of transport airplanes at Washington National Airport. Results regarding gusts, rolling direction, and number of engines are provided.

A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 degrees comparison is made with the results of a closed expression given in NACA-TN-2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory agreement is found for a sufficient distance downstream to include most practical missile-tail positions. The interference forces on an equal-span cruciform wing are calculated for five angles of bank (including the trivial case of zero bank) from the vortex positions found by use of the series.

Report presenting an investigation of the Reynolds number for transition on the outside of a hollow cylinder with heat transfer from the boundary layer to the wall at Mach number 6.9. At a given Mach number, it appears that the Reynolds number based on leading-edge thickness is an important parameter in comparisons of flat-plate transition data from various installations.

"Studies of various arrangements of wings and bodies designed to provide favorable wave interference at supersonic speeds lead to the problem of determining the minimum possible valve of the wave resistance obtainable by any disposition of the elements of an aircraft within a definitely prescribed region. Under the assumptions that the total lift and the total volume of the aircraft are given, conditions that must be satisfied if the drag is to be a minimum are found. The report concludes with a discussion of recent developments of the theory which lead to an improved understanding of the drag associated with the production of lift" (p. 1).