Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a supersonic aircraft configuration equipped with a canard control surface at a Mach number of 1.89. The model had a 40 degree sweptback tapered wing with an aspect ratio of 4 and 10-percent-thick circular-arc sections normal to the quarter-chord line. Results regarding the pitching-moment characteristics, lift and longitudinal-force characteristics, longitudinal stability and control, and lateral stability characteristics are provided.

Report presenting a free-flight investigation in a range of Mach numbers to determine the maximum deflection, zero-lift rolling effectiveness, and general operating characteristics of a bellows-actuated aileron control system energized by the pitot (impact) pressure. Testing of a system with a partial-span spit-flap aileron on a 60 degree delta wing showed that it is promising for obtaining lateral control at supersonic speeds. Results regarding aileron rolling effectiveness, aileron hinge moments, system time lag, estimation of aileron deflection, and aileron deflection control are provided.

Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and a taper ratio of 0.50, equipped with leading- and trailing-edge flaps. The purpose of the tests was to determine the low-speed aerodynamic characteristics of the wing as affected by the separate or combined deflections of a full-span, constant-chord, leading-edge, plain flap and a partial-plan, constant-chord, trailing-edge flap of either the plain or split type. Results regarding the maximum lift characteristics, pitching-moment characteristics, drag coefficients, lift-drag ratio, and effect of Reynolds number and profile modification are provided.

Fundamental flame velocities are reported for pentane air, ethylene-air, and propylene-air mixtures for the concentration range 60 to 130 percent of stoichiometric. A form of the Tanford and Pease equation, which includes a small constant velocity term independent of diffusion, will predict the observed changes in flame velocity.

Some of the systematic research conducted by the NACA on aircraft gas-turbine combustors is reviewed. Trends depicting the effect of inlet-air pressure, temperature, and velocity and fuel-air ratio on performance characteristics, such as combustion efficiency, maximum temperature rise attainable, pressure loss, and combustor-outlet temperature distribution are described for a variety of turbojet combustors of the liquid-fuel type. These trends are further discussed as effects significant to the turbojet engine, such as altitude operational limits, specific fuel consumption, thrust, acceleration, and turbine life.

Report presenting a large wind tunnel that has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of a slotted wind tunnel has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality can be produced.

An air-cooled turbine blade with a capped leading edge was investigated in a modified commercial turbojet engine over a range of engine speed from 4000 to 11,350 rpm. The cooling performance of the caped-leading-edge configuration was superior to all leading-edge cooling modifications previously investigated.

Memorandum presenting ground tests made on the longitudinal control system in a Boeing B-47A airplane. The simulator tests showed the pilot-airplane-control-system combination to be satisfactory in spite of the relatively large phase lags noticed in the frequency-response tests. Results regarding the relation between elevator angle and stick force, relation between stick angle and stick force, relation between elevator angle and stick angle, and the simulator tests are provided.

From Summary: "An investigation was conducted on a large centrifugal compressor from an experimental turbojet engine to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal-type compressors. The results of the research conducted on the compressor indicated that the compressor would not meet the desired engine-design air-flow requirements (78 lb/sec) because of an air-flow restriction in the vaned collector (diffuser). Revision of the vaned collector resulted in an increased air-flow capacity over the speed range and showed improved matching of the impeller and diffuser components."

Transfer functions descriptive of the response of most engine variables were determined from transient data that were obtained from approximate step inputs in fuel flow and in exhaust-nozzle area. The speed responses of both spools to fuel flow and to turbine-inlet temperature appeared as identical first-order lags. Response to exhaust-nozzle area was characterized by a first-order lag response of the outer-spool speed, accompanied by virtually no change in inner-spool speed.