Report presenting an investigation by the transonic-bump method of the static longitudinal aerodynamic characteristics of a series of swept, highly tapered, thin wings in the high-speed 7- by 10-foot tunnel. Testing occurred over a range of Mach and Reynolds numbers and angles of attack. Results regarding lift and drag characteristics and longitudinal stability characteristics are provided.

Memorandum presenting an investigation in the 7- by 10-foot tunnel of the static longitudinal and lateral stability characteristics of a model with an unswept wing and several different tail arrangements. The shapes tested include a Y-tail, a cruciform tail, and a more conventional T-tail. Results regarding wing-body characteristics, effects of stabilizer incidence on lateral characteristics, T-tail characteristics, Y-tail characteristics, X-tails, estimated tail contribution, and characteristics referred to the body-axis system are provided.

Report presenting shadowgraphs of flow patterns through the blade passage and ahead of a compressor rotor by shining parallel light rays approximately radially onto a rotor hub and upstream inner ring, which was painted white to serve as a screen. The flow patterns were used in conjunction with measured data to analyze the performance of two axial-flow supersonic compressors over a range of Mach numbers in Freon-12. The shadowgraph was found to be a useful tool for comparing the flow patterns within rotors and cascade sections and improving compressor analysis.

Report presenting pressure-distribution data on fuselage surfaces which extended downstream of a jet exit and were subject to the influence of a heated propulsive jet. Testing occurred at a range of free-stream Mach numbers, jet pressure ratios, and jet-exit temperatures.

Report presenting an investigation using a number of systematic configuration modifications to an afterburner to determine their effect on screech characteristics. The modifications included changes in the afterburner diffuser, the fuel system, and the flame holder. Results regarding some of the characteristics of screeching combustion, effect of diffuser flow conditions, and effect of fuel system and flame holder are provided.

A brief investigation was made of the longitudinal-stability characteristics of a YF-84A airplane (Army Serial No. 45-79488). The airplane developed a pitching-up tendency at approximately 0.80 Mach number which necessitated large push forces and down-elevator deflections for further increases in speed. In steady turns at 35,000 feet with the center of gravity at 28.3 percent mean aerodynamic chord for normal accelerations up to the maximum test value, the control-force gradients were excessive at Mach numbers over 0.78. Airplane buffeting did not present a serious problem in accelerated or unaccelerated flight at 15,000 and 35,000 feet up to the maximum test Mach number of 0.84. It is believed that excessive control force would be the limiting factor in attaining speeds in excess of 0.84 Mach number, especially at altitudes below 35,000 feet.

Report discussing an investigation to determine the aerodynamic characteristics of hypersonic missile configurations with cruciform trailing-edge flaps with all-movable control surfaces. The all-movable controls were found to produce much larger values of trim lift and normal acceleration than the trailing-edge-flap configuration.

"An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the normal loading were determined. Tests of the model in the long-range loading also were made" (p. 1).

From Summary: "Wind-tunnel tests were made of a 1/25 scale model of the Martin JRM-1 airplane to determine: (1) The longitudinal stability and control characteristics of the JRM-1 model near the water and lateral and directional stability characteristics with power while moving on the surface of the water, the latter being useful for the design of tip floats; (2) The stability and stalling characteristics of the wing with a modified airfoil contour; (3) Stability characteristics of a hull of larger design gross weight; The test results indicated that the elevator was powerful enough to trim the original model in a landing configuration at any lift coefficient within the specified range of centers of gravity."

From Summary: "Tests of a model of the XJR2F-Y amphibian were made in Langley tank no. to determine the spray characteristics and the take-off and landing stability. At a gross load of 22,000 pounds full size, spray entered the propeller disk only at a very narrow range of speeds. The spray striking the flaps was not excessive and no appreciable wetting of the tail surfaces was noted. The trim limits of stability appeared to be satisfactory and the upper-limit porpoising was not violent."

From Summary: "Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant properties based on the coolant bulk temperature gave the best agreement with experimental data."

The available foreign and American data relating to Reynolds number effects on the maximum lift coefficients of swept-back wings are summarized and discussed. The data show that at low Reynolds numbers (below about 2.0 x 10(exp 6)) higher maximum lift coefficients were measured in most cases for moderately swept-back wings than for unswept wings of similar plan form; at high Reynolds numbers, however, increasing sweepback resulted in decreasing maximum lift coefficients. A smaller rate of increase of the maximum lift coefficient with Reynolds number was measured for the swept-back wings than for similar unswept wings in the critical range of Reynolds number. Increasing the Reynolds number resulted in decreases in the maximum lift coefficients of the two wings of approximately triangular plan form that were investigated.

Report presenting an investigation to determine the reductions in temperature-recovery factor associated with pulsating flows generated by spike-nose cylinders. The investigation was conducted at zero angle of incidence at a free stream Mach number of 3.50 and a free stream Reynolds number of 1.73 million.

Report presenting an investigation on an airplane model with drooped horizontal tail and a highly tapered wing of aspect ratio 2.8 and 45 degrees of sweep. The primary purpose of the investigation was to determine what improvements in the control of leading-edge stall would be possible with the use of area suction on a leading-edge flap and with the leading-edge flap used with a modified or bulbous leading edge and chord extension.

Report presenting a transonic flutter investigation of models of a wing of a new fighter airplane with an arrowhead plan form, ailerons at the tips and flaps, and was cantilever mounted. Results regarding the run, point, panel behavior, scaling, and a comparison of the basic, modified, and locked ailerons are provided.

"Investigations were made of the turbine from a Mark 25 torpedo to determine the performance of the unit with three different turbine nozzles at various axial nozzle-wheel clearances. Turbine efficiency with a reamed nondivergent nozzle that uses the axial clearance space for gas expansion was little affected by increasing the axial running clearance from 0.030 to 0.150 inch. Turbine efficiency with cast nozzles that expanded the gas inside the nozzle passage was found to be sensitive to increased axial nozzle-wheel clearance" (p. 1).

Report presenting an investigation of the jet effects on several afterbody shapes of a single-engine fighter-airplane model in the 16-foot transonic tunnel at a range of Mach numbers and angles of attack. The afterbody-geometry variables were boattail angle, afterbody length, and base area. Results regarding evaluation of support interference, afterbody-pressure-distribution characteristics, and drag characteristics are provided.

From Introduction: "This report describes some measurements of these quantities obtained by crashing fighter aircraft under circumstances approximating those observed in service."

"Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was determined in investigations of the complete engine in the NACA Cleveland altitude wind tunnel. Characteristics are presented as functions of the total-pressure ratio across the turbine and of turbine speed and gas flow corrected to sea-level conditions. Three turbine nozzles of different areas were used to determine the area that gave optimum performance" (p. 1).

The performance of a mixed-flow impeller in combination with a semivaneless diffuser were experimentally investigated. The diameter of the impeller was 11.0 inches and a maximum tip diameter of 14.74 inches. The semivaneless diffuser had an overall diameter of 28.00 inches. The performance properties of the mixed-flow impeller were also investigated with a 34.00 inch vane loss diffuser having a transition section of the same geometry as the semivaneless diffuser.

From Summary: "In order to improve the tracking characteristics of an automatic interceptor, a revised roll-command computer was tested both on an analog computer and in flight. This report presents flight-test results which indicate a significant improvement in flight-path stability and tracking accuracy. The modified roll computer was designed on the basis of previous analytical studies."

Report presenting an investigation of a free-flight test vehicle to obtain boundary-layer-transition and heat-transfer data. The model had a 15-degree-included-angle cone-cylinder and a 10 degree conically flared afterbody. Results regarding the free-stream conditions, conditions at outer edge of boundary layer, temperatures and heat-transfer coefficients, and boundary-layer stability conditions are provided.

Report presenting the results of an investigation of the static lateral-directional stability characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for various combinations of the canard, body, wing, and vertical tail. Data were obtained at a variety of angles of attack, sideslip angles, and canard angles.

An investigation was conducted to determine the operational and performance characteristics of the TG-100A gas turbine-propeller engine II. Windmilling characteristics were deterined for a range of altitudes from 5000 to 35,000 feet, true airspeeds from 100 to 273 miles per hour, and propeller blade angles from 4 degrees to 46 degrees.