Describes the characteristics of the different breeds of chicken that are used for the production of meat and eggs.

A guide to growing, harvesting, and selling peanuts. Includes descriptions of peanut varieties.

Memorandum presenting an investigation of the performance of inlet configurations with a forebody designed for isentropic external compression at a nominal Mach number of 5.6. At zero angle of attack, all the configurations yielded larger total-pressure recoveries than had previously been obtained with a single-conical-shock inlet. Results regarding the flow about the forebody, inlet performance, and performance comparisons are provided.

An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.

Sea-level static testing of turbojet engine afterburner.

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.

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 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 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.

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 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.

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.

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.

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 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.

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."

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 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 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.

"An experimental investigation has been conducted to determine the dynamic stability and control characteristics in hovering and transition flight of a 0.13-scale flying model of the Convair XFY-1 vertically rising airplane with the lower vertical tail removed. The purpose of the tests was to obtain a general indication of the behavior of a vertically rising airplane of the same general type as the XFY-1 but without a lower vertical tail in order to simplify power-off belly landings in an emergency. The model was flown satisfactorily in hovering flight and in the transition from hovering to normal unstalled forward flight (angle of attack approximately 30deg)" (p. 1).

"A 1/10-scale rocket model of the Lockheed XF-104 with faired inlets has been flown over a Mach number range from 0.80 to 1.45 to determine low-lift drag and a limited amount of stability data. The center-of-gravity locations were 4.0 and 1.5 percent of the mean aerodynamic chord before and after sustainer firing, respectively. Oscillations induced by pulse rockets were used to determine stability data. The external transonic drag coefficient increased from a value of 0.0160 at Mach number 0.80 to a maximum of 0.0432 near Mach number 1-13, with a drag rise Mach number of about 0.93. At Mach numbers where it could be determined, the model exhibited stable dynamic and static stability characteristics at low lift" (p. 1).

Report presenting an exploratory investigation of three aluminum disoaps of C(sub 8) acids to determine the gelling properties and stabilizing ability in slurries of 50 percent magnesium power and JP-4 fuel. All of the soaps were found to gel the slurries satisfactorily and to exhibit adequate reproducibility of gel properties. Results regarding the soap behaviors, effects of temperature, viscosity, and formation of the gel structures are provided.

Memorandum presenting pulse techniques applied to strain gages for increasing the output level and extending the usable range. Bonded and unbonded strain gages which normally operate with exciting potentials between 3.5 and 14 volts operated satisfactorily with 200-volt pulses of 1-microsecond duration and a repetition rate of 350 per second. Results regarding maximum allowable voltages, effective pulse duration, sensitivity, minimum readable signal, effects of cable capacitance and inductance, sensitivity to external noise, and linearity are provided.