Memorandum presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.

Memorandum presenting various reports regarding the use of hydrogen for turbojet and ramjet powered flight. Some of the characteristics considered include the combustion properties, potential fueling problems, and flight experience with hydrogen on-board.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects on the static longitudinal stability and control characteristics of various modifications to a 0.065-scale model of the Chance Vought Regulus II missile. Some of the modifications included control housing on top of the fuselage, two sizes of canard surfaces with fixed incidence angles, various angles of nose droop, and two types of inlet boundary-layer bleed diverters.

Report presenting a flight test conducted to determine the minimum drag of a 0.11-scale rocket-boosted model of the Chance Vought XF8U-1 airplane with a transonic-area-rule fuselage-cross-sectional-area development. Results regarding the trim normal-force coefficient and measured drag are provided.

Memorandum presenting the Bell X-5 research airplane tested at 58.7 degrees sweepback during the program to determine the characteristics of a variable-sweep fighter airplane at transonic speeds. This paper includes the stability and control characteristics in the stable lift range up to Mach numbers near 1.0 at an altitude of 40,000 feet and to slightly lower Mach numbers at altitudes of 25,000 feet and 15,000 feet. Results regarding general comments, static stability and control characteristics, and longitudinal dynamic stability are provided.

Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.

Report presenting a free-jet investigation of the performance, burner-shell cooling, and ignition characteristics of a flight-weight 48-inch-diameter XRJ47-W-5 ramjet engine at an inlet Mach number of 2.75 and an angle of attack of 3 degrees. Data were obtained over a range of altitudes, inlet temperatures, and fuel-air ratios.

Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.

Performance of experimental annular turbojet combustors at simulated high altitude supersonic flight conditions.

Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.

An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.

Memorandum presenting the tail-pipe fuel ratio, mass flow of combustion gas, and radial fuel flow distribution on cooling requirements of tail-pipe burner with annular cooling-air passage.

Report presenting a theoretical study of the possibility of improving the lifting efficiency of aircraft flying at supersonic speeds using indirect lift, which can be induced on the wing by the fuselage shape and/or wing end plates. Results indicated that lifting efficiency of a planar wing may be improved by favorable interference induced by lateral forces on the end plates or on the sides of the fuselage.

"The results of an investigation of several internal water-inertia-separation inlets consisting of a main duct and an alternate duct designed to prevent automatically the entrance of large quantities of water into a turbojet engine in icing conditions are presented. Total-pressure losses and icing characteristics for a direct-ram inlet and the inertia-separation inlets are compared at similar aerodynamic and simulated icing conditions. Complete ice protection for inlet guide vanes could not be achieved with the inertia-separation inlets investigated" (p. 1).

Memorandum presenting a wing-root inlet configuration in which inlet components were varied and was tested in the 4- by 4-foot supersonic pressure tunnel at 3 Mach numbers. Angles of attack and sideslip ranges were also varied. Inlet performance and engine-flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed.

"An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability" (p. 1).

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.

Report presenting the lift and drag characteristics of a 60-degree delta-wing interceptor airplane with fuselage extension and indentation at a range of Mach numbers and altitudes. A comparison with a prototype airplane and a comparison of the flight results with the model tests are provided.

Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.

Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.

Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.

Report discussing an investigation of the McDonnell XF3H-1 with models to determine the aerodynamic effects of operating internally stowed extensible rocket racks during transonic flight. Information about the flutter, static longitudinal stability, dynamic longitudinal stability, static directional stability, trim, drag, and effect of rocket racks on aerodynamic characteristics of the model is provided.

"An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects on the static longitudinal stability and control characteristics of various modifications to a 0.065-scale model of the Chance Vought Regulus II missile. The modifications consisted of a control housing on top of the fuselage, two sizes of canard surfaces with fixed incidence angles, various angles of nose droop, and two types of inlet boundary-layer bleed diverters. The tests were made at a Mach number of 2.01 and a Reynolds number, based on the mean aerodynamic chord of 1.54 x 10(exp 6)" (p. 1).

Memorandum presenting an analysis of a system consisting of a mercury turbine-driven air compressor a mercury condenser wherein heat was added to the compressed air. The heat addition to the mercury is accomplished in an intermediate heat exchanger (mercury boiler) which has a liquid metal, other than mercury, circulating through the opposite side and through a nuclear reactor. Results regarding the turbine-exhaust pressure, turbine-inlet pressure, condenser-inlet Mach number, effect of nacelle drag, and some general data are provided.