Report presenting analytical methods to calculate average and local turbine-blade temperatures. The temperatures were compared with experimental data obtained in a forced-convection, water-cooled aluminum turbine over a range of turbine-inlet-gas temperatures and coolant-mass velocities. Results regarding comparison of calculated and experimental aluminum turbine blade temperatures, comparison of calculated and experimental stationary-blade temperatures, stationary water-cooled blade operating data, and turbine operating data are provided.

Memorandum presenting an investigation of the rolling effectiveness of a partial-span, perforated spoiler on a wing with 45 degrees of sweepback at Mach numbers from 0.25 to 0.96. The effects of the spoiler on the lift, drag, and pitching moment were also determined. Results regarding Reynolds number, Mach number, and predicted rate of roll are provided.

Report presenting a wind-tunnel investigation at low speeds to determine the lateral-control and hinge-moment characteristics of a 20-percent-chord, unsealed, partial-span outboard aileron equipped with an overhang, a paddle, or a spoiler balance on a tapered 51.3 degree sweptback semispan wing model with an aspect ratio of 3.05. The aileron effectiveness was not greatly affected by the overhang or paddle balance, but the spoiler balance increased the effectiveness obtained with the plain flap.

Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.

Report presenting an investigation of a sweptback wing in combination with a fuselage of a type considered suitable for long-range, high-speed airplanes in the 12-foot pressure wind tunnel. The investigations included tests of the wing alone, the wing-fuselage combination, and the effects of fences.

Memorandum presenting a description of a method of telemetering skin temperature using a small resistance wire pickup with a time constant of less than 0.003 second to determine boundary-layer heat-transfer coefficients. An evaluation of the accuracy of the method of measuring the heat-transfer coefficient is given for a particular application.

Report presenting a low-speed wind-tunnel investigation to determine the high-lift characteristics of a thin delta wing equipped with a single and double slotted trailing edge flap. Results regarding the lift, drag, and pitching-moment characteristics of the plain wing and various flap configurations are provided. The maximum lift coefficient of the model could be increased from 1.45 for the plain wing to 1.86 when the double slotted flap was deflected to 50 degrees.

"The drag and pressure recovery of a scoop-inlet model have been investigated at transonic speeds by the free-fall testing technique over a Mach number range from about 0.8 to 1.12. Tests were conducted at zero angle of attack, using both rounded and sharp lips at mass-flow ratios from about 0.6 to 0.9. The results indicate that the Mach number of drag divergence of the scoop-inlet model was about the same as that of the basic model without inlets which was tested previously" (p. 1).

Report presenting an investigation of the accuracy of a currently used method for predicting the dynamic lateral oscillatory characteristics of airplanes. The study involved the comparison of controls-fixed flight-test data from several current fighter-type jet airplanes with the calculated values of period and damping for the airplanes.

Report presenting an experimental investigation to determine some of the characteristics of an inset tab as an aerodynamic balance in the Mach number range between 0.7 and 1.4 using a zero-lift rocket-propelled model in free flight. Results regarding the variation of the aileron floating angle, the wing-tip helix, the balancing effect, and the penalty occurred throughout the Mach number range are provided.

Report presenting an investigation of the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 in a free-jet facility over a range of simulated altitudes. Results regarding the diffuser characteristics, combustor performance, thrust output, and operational characteristics are provided.

Report presenting pressure distributions and wake measurements for wings with 30 and 45 degrees of sweepforward, in conjunction with a midwing fuselage, at Mach numbers up to 0.96. The wings had an NACA 65-210 section, a taper ratio of 0.38, and aspect ratios of 7.5 and 5.2. Results regarding pressure distributions, wake measurements, and corrections are provided.

Report presenting an investigation of the hydrodynamic characteristics of a model of a 130,000-pound transonic flying-boat design with a high length-beam ratio planing-tail hull, sweptback gull wings with wing-tip floats, and wing-root jet-power-plant installation. Results regarding the aerodynamic, hydrostatic, and hydrodynamic qualities are provided.

Report presenting an investigation to determine the aerodynamic characteristics of a wing-fuselage configuration with a wing with quarter-chord line swept back 35 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Lift, drag, and pitching-moment characteristics, downwash angles, and wake characteristics for various angles of attack and Mach numbers are provided.

Report presenting the results of static tests conducted for the purpose of determining the lift forces and hinge moments associated with a flat-plate paddle vane, externally hinged near a rocket-nozzle exit and operating on the jet for vane deflection angles ranging from -4 degrees to 25 degrees. Results regarding vane aerodynamic characteristics, performance of rocket motor, and vane erosion

An experimental investigation was made at Mach number 1.90 of the performance of a series of perforated convergent-divergent supersonic diffusers operating with initial boundary layer, which was induced and controlled by lengths of cylindrical inlets affixed to the diffusers. Supercritical mass-flow and peak total-pressure recoveries were decreased slightly by use of the longest inlets (4 inlet diameters in length). Combinations of cylindrical inlets, perforated diffusers, and subsonic diffuser were evaluated as simulated wind tunnels having second throats. Comparisons with noncontracted configurations of similar scale indicated conservatively computed power reductions of 25 percent.

Report presenting the vibration characteristics of several symmetrical ball-root-type blades simulating the mass and natural frequency of axial-flow-compressor blades under various mounting conditions by subjecting them to controlled periodic excitation and centrifugal loading. Results regarding loose single ball-root mounting, loose-lubricated, single ball-root mounting, double ball-root mounting, and damping measurements are provided.

Memorandum presenting wind tunnel tests to determine the aerodynamic characteristics of a semispan wing with a modified NACA 0012-64 section and a 26.6-percent-chord, plain, trailing-edge aileron. Results are shown for the wing with the 0.229-chord line unswept and swept back 45 degrees and for a Mach number range from 0.40 to 0.925.

Report discussing an investigation using rocket-propelled vehicles in free flight to determine the effect of fuselage-diameter - wing-span ratio on the damping-in-roll characteristics of delta wings at a range of Mach numbers. The damping-in-roll derivative was found to decrease when the fuselage-diameter - wing-span ratio was increased. The experimental results are compared to calculated values.

Memorandum presenting an investigation of the stability and controllability in space of an arrangement comprising a man standing on a small platform which is rigidly connected to a jet nozzle with its thrust axis perpendicular to the platform and its thrust opposed to the pull of gravity. Results regarding the initial flights with the platform, flights with landing gear, flights with landing gear and inertia, flights with landing gear and gyroscope, flights with landing gear and control stick, flights with landing gear and seat, and discussion of the balancing process are provided.

Memorandum presenting an investigation conducted with an NACA submerged inlet at Mach numbers from 1.17 to 1.99. Total-pressure ratio, mass-flow ratio, and static pressure distribution along the ramp and main body were obtained at angles of attack of 0 and 6 degrees for a side inlet location. The results showed that the maximum total-pressure ratio attainable with the submerged inlet decreased from 0.83 at a Mach number of 1.17 to 0.52 at a Mach number of 1.99.

Report presenting an investigation in the free-spinning tunnel to study the behavior in descent of hemispherical and quasi-conical parachutes, some with symmetrical canopy modifications and all with a right circular cylinder suspended by one end below the parachute. Results indicated that a lateral flight component during descent could be obtained by using a circular cutout in the side of the canopy of a hemispherical parachute and a large slit between two panels of a quasi-conical parachute.

From Introduction: "Altitude-chamber and wind-tunnel investigations of the performance of turbojet engines such as those reported in references 1 to 4 have shown that the conventional correction factors fail to generalize the engine performance variables at high altitudes. An investigation was therefore made at the NACA Lewis laboratory to determine the altitude performance of the J33-A-23 turbojet engine and to demonstrate the magnitude of departure of actual altitude performance from that predicted from sea-level performance."

Report presenting an investigation in an altitude chamber to determine the power extraction and braking characteristics of a windmilling single-spool axial-flow turbojet engine of the 5000-pound thrust class over a range of altitudes and Mach numbers. Results regarding extractable horsepower from a windmilling engine, total pressure gradient through a windmilling engine, contribution of a compressor to extracted horsepower, and braking of the windmilling engine are provided.