Report discussing tests on a helicopter rotor powered by ram-jet engines located at the rotor blade tips. Information about the basic hovering characteristics of the rotor and the propulsive characteristics of the ram-jet engine were obtained over a range of speeds and fuel rates. Results were also obtained in the power-off condition and with the engines removed.

Memorandum presenting an investigation of a can-type flame holder employing a fuel-air-mixture control sleeve in a 20-inch-diameter ramjet combustor conducted by free-jet and direct-connect techniques at a simulated flight Mach number of 3.0 and altitudes from about 70,000 to 80,000 feet. Results regarding the effect of shortening combustion chamber and effect of pilot-burner variables are provided.

Memorandum presenting an investigation of the effect of the number and width of annular flame-holder gutters on afterburner performance in a 26-inch-diameter afterburner test rig. The burner inlet temperature was held at 1250 degrees Fahrenheit. Results regarding the effect of gutter width on stability limits and effect of flame-holder blockage on pressure drop are provided.

Report presenting an investigation of the effects of afterburner-inlet total temperature, total pressure, velocity, fuel-air ratio, and afterburner combustion-chamber length on afterburner performance and stability limits using a cylindrical afterburner installed in a duct test rig. The afterburner was investigated over a range of total temperature, total pressure, velocity, and afterburner fuel-air ratios.

Report presenting flight tests to determine the causes of undesirable dynamic lateral-stability characteristics of an airplane. Various rudder modifications were flight tested with the rudder free and fixed over an indicated airspeed range from approximately 200 to 450 miles per hour. Results regarding rudder-fixed characteristics and rudder-free characteristics are provided.

Report presenting 1/12-size model of a streamline fuselage modified by patterns of air jets or strips on the fuselage bottom. The effects of spacing of jets, length of jet rows, and direction of jets were determined for a simulated chine configuration. Data are presented on resistance, trim, effective hydrodynamic lift, and spray.

The performances of Navy Jet Mix and MIL-F-5624A (JP-3) fuels were compared in J33, J47, and NACA experimental annular combustion chambers. Combustion efficiencies, altitude operational limits, and carbon-forming tendencies wer determined and discussed. The results indicate that Jet Mix fuel can be utilized satisfactorily in a number of current turbojet engines over the normal operating range. Small differences in combustion efficiences and altitude operational limits existed between the two fuels but these differences depended on the particular combustor and simulated altitude and rotor speed condition. Excessive carbon deposition is not predicted for Jet Mix fuel, although this property may be marginal.

Report presenting an investigation of the effect of the number and width of annular flame-holder gutters on afterburner performance in a 26-inch-diameter afterburner test rig. A 1-ring, 2-ring, and two 3-ring flame holders were investigated over a range of fuel-air ratios. Results regarding the effect of number of annular v-gutters on combustion efficiency, effect of gutter width on stability limits, and effect of flame-holder blockage on pressure drop are provided.

Report presenting an investigation of the effectiveness of transpiration cooling on an 8 degree total-angle conical body with a porous skin for various coolant mass flow rates of nitrogen gas, helium gas, and distilled water.

Report presenting seven pairs of wings tested at Mach numbers of 1.63, 1.93, and 2.41 to determine the validity of NACA TN 2858, which predicts that delta wings with linearly varying thickness ratio have less wave drag than a constant-thickness-ratio delta wing. Results regarding the zero-lift wave drag, values of lift, total drag, pitching moment, and lift-drag ratios for an angle of attack range are provided.

Report presenting the effect of fuel properties on combustion-liner temperatures in a single tubular combustor at combustor-inlet conditions representative of those encountered in turbojet-powered high-flight-speed aircraft. Testing was conducted with three liquid jet-type fuels that varied in voltaility and aromatic content. The variations in fuel properties were found to produce only moderate and not always consistent changes in average liner temperature.

Memorandum presenting the development of fabrication techniques to provide cast-cored turbine blades with hollow tip sections. Two types of modified cast-cored blades that provided an 11-percent weight reduction from a fully cast-cored blade and a 13-percent weight reduction from a standard uncooled blade were investigated in a turbojet engine modified for air-cooling. Results regarding the experimental heat-transfer, temperature comparison with other cooled-blade configurations, calculated and experimental blade temperatures, cooling-air pressure drop, and structural reliability are provided.

The crystal structures of alloys 61, X-40,X-50, 422-19, 6059, and Vitallium, derived from x-ray diffraction, are discussed. The alloys have been, or are being considered for use in gas turbine applications. The predominant phase was a solid solution of the face centered cubic type of the principal constituent elements.The lattice parameters were found to be between 3.5525 and 3.5662.

From Introduction: "The purpose of this report is to present the results of an analytical investigation of the engine characteristics of two-spool engines with high over-all compressor pressure ratio (12.0 at design). Some of the turbine design problems encountered in a single-spool engine with current compressor pressure ratio (7.32 at design) were investigated in reference 1. The investigation was extended in reference 2 to cover the effect of mode of engine operation on the turbine design requirements and engine performance for a single-spool engine with current compressor pressure ratio."

Memorandum presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails with unswept and 35 degree sweptback plan forms. The two models had an aspect ratio of 4.5, taper ratio of 0.5, and an NACA 64A010 airfoil section. Test results are presented with and without standard roughness applied to their leading edges and with sealed and unsealed radius-nose elevators.

Report presenting an investigation in the supersonic wind tunnel on a cylindrical-shroud ejector. Data were obtained at several weight-flow ratios, primary pressure ratios, and free-stream Mach numbers. The results indicate that there was no effect of free-stream Mach number on the pumping characteristics of an ejector of this type. Results regarding the internal characteristics and external characteristics are provided.

From Introduction: "The combustor efficiency, combustor total-pressure ratio, combustor-outlet total pressure, combustor-inlet Mach number, and specific fuel consumption are presented. The effect of combustor length on efficiency and the effect of pilot operating conditions burning limits are also presented."

From Summary: "In order to determine the conditions of engine operation causing the most severe thermal stresses in the hot parts of a turbojet engine, a J47-25 engine was instrumented with thermocouples and operated to obtain engine material temperatures under steady-state and transient conditions. Temperatures measured during rated take-off conditions of nozzle guide vanes downstream of a single combustor differed on the order of 400 degrees F depending on the relation of the blades position to the highest temperature zone of the burner. Under the same operation conditions, measured midspan temperatures in a nozzle guide vane in the highest temperature zone of a combustor wake ranged from approximately 1670 degrees F at leading and trailing edges to 1340 degrees F at midchord on the convex side of the blade."