"An experimental radial-survey investigation of the J71-97 three-stage turbine equipped with a first stator having a throat area 87 percent of the design value was conducted at one turbine operating point. The first-, second-, and third-stage mass-averaged efficiencies were 0.897, 0.843, and 0.755, respectively. The corresponding over-all turbine efficiency was 0.856" (p. 1).

Report presenting an investigation using a small-scale ramjet combustor to determine the conditions for spontaneous ignition of pentaborane, amyl nitrate, propylene oxide, and JP-4 fuel. For the range of conditions investigated, the threshold of spontaneous ignition of pentaborane is primarily governed by temperature and is also influenced by burner length and configuration. Combustion efficiency was found to increase in burner length and blocked area of the flame holder.

Memorandum presenting an investigation at high subsonic speeds of a model of a twin-engine swept-wing fighter-type airplane. The model was tested with several different tail configurations and with several wing and engine inlet modifications. Results regarding pitching-moment characteristics, lift and drag characteristics, and lateral derivatives are provided.

Memorandum presenting the results of an investigation directed at determining the effectiveness of various amounts and spanwise extents of conical camber on the aerodynamic characteristics of a wing-body-tail combination employing a triangular wing of aspect ratio 2.2. Five cambered wings were tested, all of which were designed for a Mach number of 1.0. Results regarding drag characteristics and lift and moment characteristics are provided.

Report presenting a low-speed wind-tunnel investigation of a high-wing airplane with an aspect ratio of 6.75 and 36 degrees of sweepback on the quarter-chord line in order to determine the lift increments obtainable with area-suction flaps. Comparisons were made to the slotted flaps normally used. Results regarding the flap lift, maximum lift and stability, and boundary-layer control requirements are provided.

A turbine blade with a porous stainless-steel shell sintered to a supporting steel strut has been fabricated for tests at the NACA by Federal-Mogul Corporation under contract from the Bureau of Aeronautics, Department of the Navy. The apparent permeability of this blade, on the average, more nearly approaches the values specified by the NAGA than did two strut-supported bronze blades in a previous investigation. Random variations of permeability in the present blade are substantialy greater than those of the bronze blades, but projected improvements in certain phases of the fabrication process are expected to reduce these variations.

An investigation to determine the altitude performance of the J57-P-1 turbojet engine and components was conducted at the NACA Lewis altitude wind tunnel. Data were obtained over a corrected inboard rotor speed range from 56 to 106 percent of rated speed, with intercompressor bleeds both open and closed, at altitudes from 15,000 to 50,000 feet and at a flight Mach number of 0.81. The corresponding range of Reynolds number indices was from 0.858 to 0.213. All data presented were obtained with a fixed-area exhaust nozzle sized according to the manufacturer's specification. Over-all engine performance parameters are presented as functions of inboard rotor speed corrected on the basis of engine inlet temperature. Component parameters are presented as functions of their respective corrected rotor speeds. A tabulation of all performance data is included in addition to the graphical presentation. Corrected net thrust is unusually sensitive to changes in corrected inboard rotor speed in the high speed region. A change of 1 percent in speed, at sated speed, produced a change of 6 percent in corrected net thrust . At rated engine speed, increasing the altitude from 15,000 to 50,000 feet at a constant flight Mach number of 0.81 increased the specific fuel …

Report presenting an investigation of an axial-discharge impeller in combination with a 16-vaned supersonic diffuser cascade over a range of flow conditions at equivalent tip speeds varying from 800 to 1600 feet per second. Results regarding the overall performance of the combination, starting of diffuser cascade, use of flow bleedoff to aid starting, radial distribution of flow angle, flow characteristics within diffuser, and efficiency of diffuser cascade are provided.

Fuels having Reid vapor pressures of 6.3 and 1.0 pounds per square inch were investigated in a tail-pipe burner on an axial-flow-type turbojet engine at a simulated flight Mach number of 0.6 and altitudes from 20,000 to 45,000 feet. With the burner configuration used in this investigation, having a mixing length of only 8 inches between the fuel manifold and the flame holder, the low-vapor-pressure fuel gave lower combustion efficiency at a given tail-pipe fuel-air ratio. Because the exhaust-nozzle area was fixed, the lower efficiency resulted in lower thrust and higher specific fuel consumption. The maximum altitude at which the burner would operate was practically unaffected by the change in fuel volatility.

Report presenting a preliminary analytical evaluation of the air and fuel specific-impulse characteristics of octene-1, aluminum, and aluminum-octene-1 slurries. The adiabatic combustion flame temperature, combustion equilibrium-gas composition, air specific impulse, and fuel-weight specific impulse are presented for each fuel. Aluminum-octene-1 slurries were found to offer a means of increasing the limited air specific impulse values available with octene-1 or hydrocarbon-type fuels.

Report presenting a method for applying the limited contraction ratio to obtain the maximum allowable blade thickness of a two-dimensional model of a supersonic-compressor rotor.

Memorandum presenting an investigation conducted to determine experimentally turbine-nozzle-blade and turbine-bucket temperatures in a turbojet engine and to correlate these temperatures with the gas temperatures. Data were obtained over the normal range of engine speeds and with two tail-pipe-nozzle areas. Results regarding basic data, turbine-nozzle-blade temperature distribution, turbine-bucket-temperature distribution, temperature distribution of gas at burner-outlet, turbine-bucket temperatures during starting, and relation of material and gas temperatures are provided.

Report presenting an extensive collection of lift and hinge-moment characteristics of control surfaces up to a Mach number of 0.90 in a high-speed wind tunnel. A wide variety of control-surface profiles, plan forms, and aerodynamic balances are included. Results regarding elevator hinge moments and longitudinal control, aileron hinge moments and lateral control, control-surface characteristics, and transonic flutter are highlighted.

Report presenting the combustion efficiencies of 10 experimental jet-propulsion fuels that are approximately 200 degrees Fahrenheit cuts of five selected crudes available in large quantities in a turbojet engine combustor at altitude conditions.