Report discussing a flight test on a rocket-boosted canard aircraft with 60 degree delta lifting surfaces, twin normal-shock-type side inlets, and twin vertical tails. The drag, longitudinal stability, and duct performance data were obtained for a range of Mach and Reynolds numbers.

Report presenting the planing characteristics, as determined by tank tests, of three surfaces representative of hydro-ski forms. One surface had a rectangular plan form with a flat bottom, one had a rectangular plan form with a transversely curved bottom, and the third had a flat bottom and triangular plan form. Results are provided in the form of plots of the load on the water, resistance, trimming moment, and draft against total wetted area with speed and trim as parameters.

Report presenting a low-speed investigation in the stability tunnel to determine the effects of changes in profile and aspect ratio on the low-speed static-stability and rolling characteristics of triangular wings. The investigation was expanded to determine the effects of adding fins to the upper surface and of cutting portions from the tips of a triangular wing to form low-aspect-ratio tapered wings.

Report presenting a free-flight investigation of two rocket-powered model configurations to determine the damping in roll. The model had rectangular wings of 4.5 aspect ratio and were the same except for the airfoil sections. Results regarding rolling velocity and total-drag coefficient are provided.

From Summary: "Calculations were made to determine the influence of changes in temperature distribution and in elastic material properties on calculated elastic stresses for a typical gas-turbine disk. Severe temperature gradients caused thermal stresses of sufficient magnitude to reduce the operating safety of the disk. Small temperature gradients were found to be desirable because they produced thermal stresses that subtracted from the centrifugal stresses in the region of the rim."

Report presents the results of sound measurements at static conditions made for a two-blade 47-inch-diameter propeller in the tip Mach number range 0.75 to 1.30. For comparison, spectrums have been obtained at both subsonic and supersonic tip speeds. In addition, the measured data are compared with calculations by the theory of Gutin which has previously been found adequate for predicting the sound at subsonic tip speeds. Curves are presented from which the maximum over-all noise levels in free space may be estimated if the power, tip Mach number, and distance are known.

From Summary: "A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion. The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the blade. Because the tunnel wall acts as a plane of symmetry, the measured aerodynamic characteristics correspond to those of an airfoil having various angles of sweepforward and sweepback. Tests were made with the vents on the lower surface open and also with the vents sealed and the internal pressure held at -20 inches of water producing an internal pressure coefficient of -1.059."

"An investigation of the stability and control characteristics of a 1/10-scale model of a Canadian tailless glider has been conducted in the 10 Langley free-flight tunnel. The glider designated the N.R.L. tailless glider has a straight center section and outboard panels sweptback 43 deg. along the leading edge of the wing. The aspect ratio is 5.83 and the taper ratio is 0.323. From the results of the investigation and on the basis of comparison with higher-scale static tests of the National Research Council of Canada, it is expected that the longitudinal stability of the airplane will be satisfactory with flap up but unsatisfactory near the stall with flap down" (p. 1).

An investigation conducted in the icing research tunnel on a ramp type recessed fuel cell vent assembly to determine its aerodynamic, rain, and icing characteristics. Although the vent-tube openings are located in the region of maximum ramp pressure, vent-tube static pressures are marginal for a low flight speed.

Report presenting a flight investigation over a range of Mach numbers to determine the aerodynamic characteristics at low lift of a rocket model of an airplane with a 52.5 degree delta wing of aspect ratio 3.08 and NACA 65A003 airfoil sections in the streamwise direction and a low, swept horizontal tail. Results regarding the longitudinal trim, lift, drag, longitudinal static stability, damping in pitch, and directional static stability are provided.

Report presenting an investigation in the high-speed tunnel to determine the effects on the chordwise pressure and section force and moment coefficients near midspan of deflecting a flap-type control with an attached tab on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6.

Memorandum presenting a study of two jet-noise-suppression devices consisting of teeth projecting into the jet stream was conducted on a current axial-flow turbojet engine. The sound fields obtained with the toothed devices showed a slight reduction in maximum sound pressure level, compared with the sound field from a standard nozzle.

Report presenting drag and longitudinal trim characteristics at low lift of a low-tail version of the North American YF-100A airplane as obtained from the flight test of a 0.11-scale rocket model at a range of Mach numbers. Longitudinal stability data and some qualitative damping-in-pitch data are also provided.

Report presenting an investigation of the performance of pentaborane fuel at relatively low equivalence ratios using a 9.75-inch-diameter ramjet engine using pentaborane at an average equivalence ratio of approximately 0.23. Time histories of the flight conditions and combustion chamber conditions, total-temperature ratio, fuel flow, pressure recovery, thrust, propulsive thrust, and drag coefficients, and comparison with hydrocarbon fuel are provided.

"The National Advisory Committee for Aeronautics is undertaking an investigation of the flying qualities of airplanes. The work consists in the determination of the significant qualities susceptible of measurement, the development of the instruments required to make the measurements, and the accumulation of data on the flying qualities of existing airplanes, which data are to serve as a basis for quantitative specifications for the flying qualities of future designs" (p. 449).

Memorandum presenting a review of important aspects of current data on thin swept wings with bulbous leading-edge contours. The outboard concentration of a bulbous contour will generally yield most or all of the characteristics low-speed benefit attainable from the use of such a contour. Results regarding data at low speeds, data at high speeds, implications of the data regarding outboard bulbous contours, and area-rule considerations and data are provided.

Report presenting the results of fuselage-deflection measurements at three stations on the fuselage of a swept-wing bomber (Boeing B-47A) during 12 push-pull maneuvers. The results are provided in the form of coefficients expressing the fuselage deflection due to normal-acceleration loads, pitching angular-acceleration loads, pitching angular-velocity loads, and the combined effect of zero-lift loads, fuselage dead weight, and landing-gear reactions. Comparisons of the theoretical and experimental results are also provided.

Report presenting a review of the possible shock system associated with the supersonic blade elements encountered in transonic-compressor rotors. The variation of shock shape and location with operating conditions is described. Results regarding flow, estimated shock losses at maximum element efficiency, and profile losses are provided.

From abstract: The PT-750 is designed to be used in conjunction with a production tester which requires automatic recording of test data. This manual provides a source of procedures and reference material necessary in automatic recording and in use of the PT-750.

From introduction: This report covers an investigation of solid-state bonding as a technique for aluminum cladding uranium plates of 3 by 0.180-in. cross section in lengths up to 14 ft.

Abstract: "A possible mechanism for the generation of magneto-hydrodynamic whirl rings near the center of the sun is described. The organic relation of the reflection of these whirl rings at the surface of the sun to the cooling of sunspots, orientation, and polarity sequence of sunspots, prominences, flares, and faculae is delineated."

This report describes a method and apparatus used to determine the density of liquid sodium hexafluoride. The report includes a drawing of the density cell used in the experiment.

The present report was prepared to serve mainly as a resume of the AEC 1953 drilling project at Big Indian Wash, and a record of related activities up to early 1954.

"The purposes of the program being conducted under the present contract are: 1) To determine the feasibility of cladding zirconium on uranium by a direct casting process. 2) To investigate the diffusion of liquid metals in the fusion zone."