Report presenting an investigation to determine the aerodynamic characteristics in sideslip of a triangular wing of aspect ratio 2.04 in combination with a body of fineness ratio 12.5 and a vertical tail surface. The body combined with the triangular plan-form wing caused no significant changes in the lift characteristics of the wing and only a 1-percent decrease in the static margin. Results regarding the longitudinal characteristics, lateral and directional characteristics, and estimation of tail and rudder effectiveness are provided.

Report presenting transonic speed testing utilizing a rocket-powered Bell XS-1 airplane with 10-percent-thick wing and 8-percent-thick horizontal tail. Information is provided for flights up to Mach number 1.06 and altitudes of about 40,000 feet. Results regarding the variation of control-surface positions and forces and sideslip angle with Mach number, time history, rudder effectiveness, and lateral oscillations are provided.

Report presenting a wind-tunnel investigation of a semispan model of a wing swept back 63 degrees with an aspect ratio of 3.5 and a taper ratio of 0.25. The tests were conducted to evaluate the effects of Reynolds and Mach number on the aerodynamic characteristics of the wing. Results regarding the characteristics of the wing with the elevon undeflected, effectiveness of the elevon, effects of roughness strips, and effect of model deflection under varying loads are provided.

Report presenting the use of a flush-type electrical pressure cell for measuring rapidly changing aerodynamic forces on a fluttering control surface. The use of the cell is valuable for the measurement of the aerodynamic forces. Results regarding the individual cells, integrated results, resolution of aerodynamic moments, comparison of aerodynamic with inertia moments, and comparison of static and dynamic hinge moments are provided.

Tests were made to determine the loss in exhaust-jet thrust and engine power resulting from the insertion of an exhaust-gas-to-air heat exchanger in a jet-type exhaust stack of an aircraft engine. The thermal performance of the heat exchanger was also determined.

An investigation has been made in the Langley full-scale tunnel of a 47.5 degree sweptback wing-fuselage combination equipped for boundary-layer control by suction. The wing aspect ratio was 3.5, the taper ratio was 0.5 and the airfoil sections normal to the quarter-chord line were NACA 61(sub 1)-A112. Tests included the plain wing and the wing with various combinations of extensible leading-edge and split flaps.

An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.

"The data obtained from cooling tests of an R-2800-21 engine installed in a P-47G airplane were studied to determine which engine and airplane operation variables were mainly responsible for the extremely uneven temperature distribution among the 18 engine cylinders obtained at the medium and high engine-power conditions. The tests consisted of flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The results of the study showed that a flow condition in the induction system associated with the wide-open throttle position, which affected either the fuel air or charge distribution, was primarily responsible for the uneven temperature distribution" (p. 1).

"An investigation of an NACA submerged air intake was conducted on a full-scale model of a fighter-type airplane. This study was made to determine the large-scale aerodynamic characteristics of a submerged air intake proposed as the result of small-scale tests and to compare the pressure-recovery characteristics of the large- and small-scale installations. Additional tests were made to determine the effect on pressure recovery of a systematic variation of ramp divergence" (p. 1).

Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.

Given here are results of tests made in calm water at various landing attitudes, speeds, and simulated conditions of damage. It was concluded that the best ditching could be made by contacting the water as near the stall angle as possible without losing adequate control. The landing flaps should be full down. If the paratainer hatch and aft-cargo doors fail as expected in a ditching, there will be a large inrush of water into the cargo compartment which makes this location a very hazardous ditching station. The airplane will settle in the water rapidly to the level of the wings with only gradual changes in attitude. The maximum longitudinal deceleration will be between 1.2g and 1.7g in a calm-water ditching.

Memorandum presenting an investigation conducted in the full-scale tunnel to determine the longitudinal characteristics of several leading-edge and trailing-edge flap configurations and the lateral characteristics of one flapped configuration on a 45 degree sweptback wing with circular-arc sections, an aspect ratio of 3.5, and a taper ratio of 0.5. Results regarding stall studies, leading-edge flaps, trailing-edge flaps, flap combinations, rounded leading-edge modification and fences, landing-performance characteristics, and aerodynamic characteristics in yaw are provided.

Report presenting the results of pressure-distribution measurements obtained in flight over the free-blown canopy of a fighter-type airplane. The measurements were compared to those of the same canopy in wind-tunnel testing to determine the degree of correlation and effects of Mach number and distortion on the pressure distribution.

Report presenting a method for the preparation and purification of the intermetallic molybdenum desilicide was developed and its properties were determined. Chemical properties were found to be highly inert, unattacked by boiling hydrochloric acid, sulfuric acid, or aqueous sodium hydroxide, slightly attacked by nitric acid, and dissolved by molten sodium hydroxide. Other mechanical properties of the material were also provided.

Report presenting an investigation to determine the lift, drag, and pitching-moment characteristics of the NACA 0010 and 0010-64 airfoil sections at Mach numbers up to 0.91 and for a range of Reynolds numbers.

Report presenting an investigation to determine the possibility of delaying at moderate or large lift coefficients the onset of the abrupt supercritical drag rise of an airfoil section by the use of camber. Results indicated that the addition of camber to the NACA 0010 airfoil leads to significant improvements in the drag characteristics at moderately supercritical speeds .

Experimental study to determine the vibrational modes of several hollow turbine blades and a solid turbine blade of similar aerodynamic design. Results regarding the significance of nodal patterns, vibrational modes of six blade types, and the probability of excitation in some of the blades are provided.

From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."

Report presenting a wind-tunnel investigation of a semispan pointed wing of aspect ratio 1.7 with 60 degree leading-edge sweepback and 30 degree trailing-edge sweepforward with a control surface. The purpose of the investigation was to determine the effectiveness of flap-type controls at transonic and supersonic speeds. Results regarding the wing characteristics and control-surface characteristics are provided.

Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with an 18.41-inch-diameter jet nozzles. Testing occurred at a range of simulated altitudes and ram-pressure ratios. Results regarding the simulated flight performance, generalized performance, and effect of jet-nozzle area on performance are provided.

From Introduction: "The aerodynamic characteristics of a series of 10-foot-diameter propellers are being investigated in the Langley 16-foot high-speed tunnel in a comprehensive propeller research program. Using high-critical-speed NACA 16-series airfoil sections (reference 1), these propellers are designed to have Betz minimum induced-energy loss loading (reference 2) for a blade angle of 45^o at the 0.7 radius, when used as a four-blade propeller operating at an advance ratio of approximately 2.1 The ultimate purpose of the program is to determine the influence upon propeller design factors and of compressiblity; the propeller tests reported herein form part of the investigation of the effects of blade-section thickness ratio."

Ignition characteristics of AN-F-32 and two AN-F-58a fuels were studied in a single can-type turbojet combustor under air-flow conditions representing engine speeds of 1600, 2500, and 4000 rpm, altitudes from sea level to 30,000 feet, ambient temperatures at sea level from 90 degrees to minus 36 degrees F, and flight Mach numbers of 0 and 0.6. Critical fuel-flow rates for ignition increased with increase in preignition engine speed, with increase in altitude, or with decrease in sea-level ambient temperature. This flow rate appears to increase in a direct relation to decrease in fuel volatility as indicated by the 10-percent-evaporated temperature.

Memorandum presenting an investigation to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a wing with an aspect ratio of 3 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for several sets of Reynolds and Mach numbers. The results indicated that for all Mach and Reynolds numbers in the test range, no apparently flow separation existed near the leading edge of the wing for lift coefficients less than 0.3.

The effectiveness of molybdenum disulfide MoS2 as a bearing lubricant was determined at high temperature and at high speeds. A 1-inch-bore ball bearing operated at temperatures to 1000 F, a speed of 1725 rpm, and a thrust load of 20 pounds when lubricated only with MoS2-air mist. A 75-millimeter-bore cageless roller bearing, provided with a MoS2-syrup coating before operation, operated at DN values to 1 x 10(exp 6) with a load of 368 pounds.