The mean heat capacity of a sample of powdered U/sub 3/O/sub 8/ was determined as a function of temperature from measurements of heat content. A thin-walled nickel capsule containing the material was heated in an electric furnace and dropped into a water calorimeter The Mean heat capacity values calculated from the experimental data were nearly constant over the temperature range, room temperture to 250-975 deg C (482-1790 deg F). The average value was 0.074 plus or minus 0.004 cal gm/sup -1EDE/C/sup -2/ (0.074 plus or minus 0.004 Btu lb/sup -1 deg F/du p -1/). From 975-1100 deg C (1790-2012 deg F) a small rise was observed. (auth)

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Report presenting a review of the status of instruments suitable for the measurement of the meteorological factors conducive to aircraft icing. Nine instruments which appear to be the most promising for obtaining meteorological data are discussed and recommendations for their continued use and development are provided.

Memorandum presenting a study of a body of revolution with an NACA 1-50-100 nose inlet at zero angle of attack and no internal air flow to study the pressure drag of an extremely blunt-nose body and comparison with previous results for a sharp-nose body. The change from sharp to inlet nose while maintaining the same afterbody shape decreased the drag-rise Mach number from 0.94 to 0.90.

Wind tunnel tests of the 0.16-scale Douglas MX-656 model were made at low and high subsonic Mach numbers to investigate the static longitudinal- and lateral stability characteristics. The tests shows that undesirable changes in longitudinal stability at the stall were apparently caused by an altered downwash pattern at the tail. The jettisonable nose fins were highly destabilizing. Compressibility effects for the test Mach numbers were not detrimental to the longitudinal- or lateral-stability characteristics.