Report presenting an investigation using rocket-propelled model of the Convair B-58 supersonic bomber. Drag at trim lift was obtained for a range of Mach and Reynolds numbers and is compared to data from several other testing facilities.

Report presenting tables and charts of gas properties for use in thermodynamic calculations for engine cycles involving the combustion of air and any fuel or combustion of fuels containing carbon, boron, hydrogen, and oxygen. Dissociation and phase changes may be accounted for with the method presented, which does not require the presentation of separate data for each fuel-air ratio.

Report presenting an investigation to determine the aerodynamic characteristics of bodies with elliptical and triangular cross sections and to compare the data with a body with circular cross sections. Force tests to determine lift, drag, and pitching-moment characteristics as well as pressure-distribution measurements were made for an angle of attack range.

The thermal decomposition of ethylpentaborane at temperatures of 185 degrees to 244 degrees C is approximately a 1.5-order reaction. The products of the decomposition were hydrogen, methane, a nonvolatile boron hydride, and traces of decaborane. Measurements of the rate of decomposition of pentaborane showed that ethylpentaborane has a greater rate of decomposition than pentaborane.

Report presenting the average heat-transfer to the forward half of a circular cylinder measured in a blowdown jet at a stream Mach number of 4.15. Most of the tests was made at a wall-to-stagnation temperature ratio of about 0.8. Report presenting pressure distributions, heat transfer and recovery temperatures, and effect of yaw on transition are provided.

Memorandum presenting an investigation utilizing a 1/15-scale rocket-propelled model of the Convair B-58 supersonic bomber. The drag at model trim lift was obtained at a range of Mach and Reynolds numbers. A comparison of the drag at transonic speeds and approximately the same Reynolds number showed excellent agreement.

Memorandum presenting an investigation made to determine the effects of lip bluntness, camber, and leading-edge roundness on the drag and pressure recovery of a normal-shock nose inlet in a body of revolution. Surface pressure distributions over the inlet lip and forebody were also obtained. Results regarding surface-pressure distributions, external drag, and pressure recovery are provided.

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Slug ruptures at C Reactor are costing a considerable amount of production and are limiting reactor power levels. A large portion of this production is lost because the ``quickie`` procedure cannot be used with unstruck ruptures. Currently there are two reasons for this condition: Insufficient reactivity is available to recover after a rupture is removed with the ``quickie`` equipment, and if the ``quickie`` method were attempted, there would be many failures due to stuck rear caps and improperly functioning equipment. With the current emphasis being placed on improving the ``quickie`` equipment and procedures, it is reasonable to assume that in the near future nearly all unstruck ruptures can be removed with this ``quickie`` procedure. However, the C Reactor does not possess sufficient excess reactivity to recover from a ``quickie`` rupture discharge following a shutdown from equilibrium conditions. This study outlines a procedure for extending the scram recovery time at C Reactor and an economic justification for buying the added reactivity necessary to carry out the procedure.