"In order to evaluate the post combustion behavior of boric oxide, pentaborane-air mixtures, burned to completion at a combustor pressure of 3 atmospheres, were expanded through a 7.1-inch-long convergent-divergent nozzle having a 4-inch-diameter throat and an exit-to-throat area ratio of 1.68. The experimentally determined thrust performance was in good agreement with the ideal equilibrium performance at stagnation temperatures of 3300 deg R and lower. The boric oxide vapor at the combustor exit required about 400 degrees F supercooling before any condensed phase was observed" (p. 1).

"An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model simulating the Convair F-102A airplane has been made in the Langley free-flight tunnel. The model in its basic configuration and with two modifications involving leading- edge slats and an increase in vertical-tail size was flown through a lift-coefficient range from 0.7 to the stall. Only relatively low-altitude conditions were simulated" (p. 1).

Report presenting testing on the NACA 16-009 airfoil and on eight airfoils of the NACA 6A series, which shows that the chordwise loading due to lift at a Mach number of 1.0 is insignificantly affected by thickness distribution within the range of airfoil shapes presented and only slightly affected by thickness. Results regarding the experimental loading on symmetrical airfoils, method of estimating pressure distribution, experimental loadings on cambered airfoils, and scope of method are provided.

Report presenting flight measurements on a swept-wing jet aircraft to determine the effects of adding forward camber and an increased leading-edge radius on the low-speed stalling characteristics, the high-speed static longitudinal stability, and the airplane drag. The modified leading edge produced values of maximum lift somewhat greater than the slats on a normal airplane, but the stall was unacceptable because of an abrupt roll-off.

A brief summary is made of the performance of a series of variable-geometry type scoop inlets investigated at the Lewis Laboratory on a model of the X-3 airplane fuselage. Data are presented for a range of inlet mass-flow ratios over a Mach number range from 0 to 2 and from 0 degrees to 12 degrees angle of attack. Rounded-lip inlets are found to give satisfactory performance to a Mach number of 1.5. Use of sharp rather than blunt lip configurations is shown to provide considerable gains in available thrust at Mach number 2.0 but penalize take-off performance to the extent that auxiliary air intakes may be required.

Report presenting the results of an experimental investigation of three plane wings in combination with a body, which represented both low- and high-wing arrangements. The three wings had different plan forms: a tapered unswept plan form, a tapered 45 degree sweptback plan form, and a triangular plan form. Results regarding the effect of Reynolds number and effect of vertical position of the wing are provided.

Report presenting an analysis of two turbojet engines, including the component performance of the compressors and turbines, in order to determine the effect on engine performance and operation of bleeding the compressor to furnish cooling air for the turbine rotor blades. Results regarding the compressor and turbine performance characteristics and engine performance characteristics are provided.

Report presenting ignition-delay determinations of furfuryl alcohol and mixed butyl mercaptans with various white fuming nitric acids were made at several temperatures with a modified open-cup apparatus and a small-scale rocket engine of approximately 30-pounds thrust.

Report presenting data obtained from an investigation of the Douglas-D558-II airplane to determine its buffeting characteristics at high lift and supersonic speeds. From Summary: "Buffeting was encountered at normal-force coefficients greater than about 0.7 in the Mach number range from 0.96 to 1.27 but at Mach number of 1.57, a peak normal-force coefficient of 0.80 was attained with no indication of buffeting. The increase in buffet intensity with lift is very gradual at supersonic speed compared with the buffet intensity-lift variation at subsonic Mach numbers."

Report presenting an investigation to determine the effects on internal performance of several geometric variables intended to produce a short, high-performance convergent-divergent nozzle. Some of the characteristics investigated included variations in the throat-contour radius, combinations of the shape of the convergent section and throat-contour radius, divergence angle, and shape of the divergent section.

Report presenting an investigation at Mach numbers 1.9 and 3.0 to demonstrate that a central core of air of high stagnation temperature can be produced in the test section of a supersonic wind tunnel. This makes performing wind tunnel testing cheaper and controls for more variables. Results regarding the core studies at Mach number 1.9 and 3.0 and diffuser performance at Mach number 1.9 are provided.

Report presenting an investigation performed at Mach number 2.96 to study the effects of some internal boundary-layer-control systems on the pressure recovery and stability characteristics of a side inlet with half a double-shock external compression surface. Counterbody bleed did not appreciably improve the performance of the inlet, and the maximum pressure recovery obtained was 62 percent. Results regarding the inlet performance with internal bleed and inlet performance with flow injection on external compression surface are provided.

Report presenting an experimental investigation of a series of fixed-geometry exhaust nozzles which simulated a variable exit, which was conducted in the 8- by 6-foot supersonic wind tunnel at Mach numbers 0, 0.6, 1.5, 1.7, and 2.0. Gross thrust performance of the long-shroud exit configurations was considerably better than the short-shroud. Results regarding flow coefficients, thrust characteristics, flight performance analysis of data, and shroud drag are provided.

From Summary: "The exhaust of a 6-inch-diameter ram-jet engine mounted in the Lewis 1- by 1-foot, Mach 3.1 supersonic tunnel was scavenged successfully with a 6.6-inch-diameter scoop. Limiting values of exhaust-to-stream static-pressure ratios and scavenge-system total-pressure ratios were determined for complete scavenging of the products of combustion. The scavenge-system operation influenced the engine exhaust-nozzle pressures under conditions of unstable scavenge flow."

Report presenting a method for the rapid selection of a turbine design within specified aerodynamic limits. Tables are provided with the overall design parameters and velocity-diagram variables of each design. Detailed design information is also included for ranges of blade-speed parameter and exit radius ratio.

Report presenting an investigation to determine the effects of forging temperatures and solution treatments on the engine performance of Inconel 700 buckets. The buckets were tested in a J33-9 turbojet engine at 1625 degrees F in 20-minute cycles. Testing demonstrated that the buckets are capable of operating for more than 450 hours at rated speed.

Report presenting an investigation of the Reynolds number effects on an axial-flow compressor with two of the transonic inlet stages doubled as compared to the original compressor. Results regarding the long-chord-compressor performance, effect of Reynolds number on compressor performance, and a comparison of long- and medium-chord compressor performance are provided.

From Introduction: "This report presents an analytical investigation of this aerodynamic interdependence in terms of the effect of variations in the turbine specific work output, blade speed, and stage number on turbine efficiency."

Report presenting an evaluation of the postcombustion behavior of boric oxide using pentaborane-air mixtures burned to completion at a combustor pressure of 3 atmospheres expanded through a convergent-divergent nozzle. Results regarding the symmetry of flow in nozzle, behavior of liquid boric oxide in nozzle, abrupt condensation phenomena, effect of abrupt condensation on performance, and effect of oxide films are provided.

Report presenting a phenomenological relation between stress, strain rate, and temperature to account for the behavior of polycrystalline metals above the equicohesive temperature. This is because the behavior of metals at elevated temperatures is constantly becoming a more important problem. The validity of the relation suggested in the equation appears to be accurate for 7075-T6 aluminum alloy.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: The legality of crediting examination and valuation fees against premium taxes paid on workmen's compensation insurance.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Compensation of County Commissioners.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Effect of order of Nebraska County Court classifying foster children for inheritance tax purposes.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: The applicability of S. B. 92, 51st Leg., authorizing increases in the pay of precinct, county, and districts officers, to the compensation of members of the Juvenile Board.