Memorandum presenting an assessment of the importance of the addition lag of the monowing versus a cruciform shape on a missile.

Report presenting flight testing at high-subsonic and supersonic speeds at high Reynolds numbers to determine the zero-lift drag of a fin-stabilized body and a wing-body combination. The body was parabolic in profile, had a fineness ratio of 10, and a ratio of body frontal area to wing area to 0.306.

Report presenting an investigation to determine the longitudinal control characteristics of deflectable wing-tip elevators on a low-aspect-ratio, untapered, 45 degree sweptback semispan wing. The elevators had triangular and parallelogrammic plan forms and flat-plate profiles. Results include the elevator effectiveness and comparison of the elevator effectiveness of deflectable wing-tip controls and trailing-edge flap-type controls.

"A device has been developed to measure local skin friction on a flat plate by measuring the force exerted upon a very small movable part of the surface of the flat plate. These forces, which range from about 1 milligram to about 100 milligrams, are measured by means of a reactance device. The apparatus was first applied to measurements in the low-speed range, both for laminar and turbulent boundary layers. The device was then applied to high-speed subsonic flow and the turbulent-skin-friction coefficients were determined up to a Mach number of about 0.8" (p. 281).

From Summary: "Curves are presented that show the theoretical performance of the augmentation method for various amounts of water injected and the effects of varying flight Mach number, altitude, ambient-air temperature, ambient relative humidity, compressor pressure ratio, and inlet-diffuser efficiency. Numerical examples, illustrating the use of the psychrometric chart and the Mollier diagram in calculating both compressor-inlet and compressor-outlet conditions when water is injected at the compressor inlet, are presented."

From Summary: "The effects of variation in inlet-air temperature, combustion pressure, and boron or pentaborane concentration on combustion performance were discussed. It was shown how the theoretical data herein could be employed in obtaining the combustion efficiency of experimental combustors. Data were presented by which combustion efficiencies obtained with a water-quench heat balance could be adjusted for the heat of dissociation of the combustion products."

"The combustion efficiency of a 50-percent-boron-hydrocarbon slurry was evaluated in a 16-inch ram-jet burner. A peak slurry combustion efficiency of 75 percent was usually obtained, and a value of 84 percent was once measured. The connected-pipe burner was run at a simulated flight condition of Mach number 2.85 at an altitude of 68,000 feet, with a 70-percent diffuser recovery giving a burner-inlet pressure of 1 atmosphere and temperature of 570 degree Fahrenheit" (p. 1).

Report presenting an exploration of the proposition that the structural weight of supersonic missiles should be reduced by the use of pressurized, thin-wall, glass-laminated shells. A model with this type of structure was investigated in the 8- by 6-foot supersonic wind tunnel to determine the minimum internal pressure necessary to prevent panel flutter. Results regarding the empty shell and shell containing liquid are provided.

Report presenting a study to compare the maneuvering performance of a cruciform and a monowing missile. Results regarding beam riding and minimum launch range at 5000 and 50,000 feet are provided.

This investigation was made to adapt wet-process autoradiography to metallurgical samples to obtain high resolution of segregated radioactive elements in microstructures. Results are confined to development of the technique, which was perfected to a resolution of less than 10 microns. The radioactive samples included carbon-14 carburized iron and steel, nickel-63 electroplated samples, a powder product containing nickel-63, and tungsten-185 in N-155 alloy.