Report presenting a study of the acceleration characteristics of a turbojet engine equipped with variable-position inlet guide vanes in the altitude test chamber. Maximum acceleration values for 3 engines of the same model were also obtained during testing and were found to differ as much as 50 percent. Results regarding the effect of fuel step size and inlet guide vane on acceleration, effect of flight condition, reproducibility of engine acceleration, compressor pressure ratio in relation to acceleration, and acceleration with inlet air distortion are provided.
Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.
From Introduction: "This report presents the results of an analysis to determine the coolant flow and pressure requirements for a particular return-flow turbine rooter blade design utilizing hydrogen, helium, or air as the coolant."
From Introduction: "V-g records supplied the NACA by the Bureau of Aeronautics in 1948 and 1949 have provided additional material. These records are analyzed statistically in this report to the frequency of large values of acceleration and airspeed, and results are compared with the design requirements."
From Introduction: "This paper presents results of an analysis of shear, bending-moment, and torque loads measured on the vertical tail during rudder-step, rudder-pulse, aileron-roll, and steady-sideslip maneuvers. In order to assess effects of Mach number and altitude, the maneuvers were performed at altitudes of 15,000, 25,000, and 35,000 feet and Mach numbers from 0.49 to 0.82."
Report presenting an analysis made to permit a comparative evaluation of the turbine rotor cooling-air requirements with convection-cooled blades for four combustor-outlet radial gas-temperature profiles: a uniform profile, a profile representable by a complete cycle of the cosine wave using cooler gas layers near the turbine casing, a profile representable by one-half cycle of the cosine wave using cooler gas layers near the stator inner ring, and an optimum profile resulting in the absolute minimum cooling-air requirements.
Report presenting boundary-layer measurements on rocket-powered free-flight models to determine average skin-friction coefficients. The test body, NACA RM-10, was a fin-stabilized parabolic body of revolution of fineness ratio 12.2 with a blunt base to provide space for a rocket jet. Results regarding the skin-friction and boundary-layer profiles and experimental and theoretical curves are provided.
Report presenting a friction, wear, and endurance-lift study made with bonded films of mixed oxides containing lead monoxide (PbO) as the main component. The coatings lubricated over the entire temperature range, but were far more effective from 500 to 1250 degrees Fahrenheit than at the lower temperatures. Results regarding the effect of silica additions on coating formation, determination of coating composition, effect of coating thickness on friction and wear, effect of temperature on friction and wear, and endurance properties are provided.
Memorandum presenting a single J33 combustor and an experimental tubular combustor incorporating a fuel vaporizer as operated with gaseous hydrogen at temperatures slightly above the boiling point of the fuel. Data were obtained to explore possible effects of the fuel temperature on combustor performance and on the control and measurement of fuel flow.
Report presenting a method for calculating the path of a jettisonable nose section at any speed by means of successive approximations using static aerodynamic characteristics. Conditions for consideration, including the effect of stabilizing fins, are included in the calculations.
Report presenting an attempt to determine the reliability and calibration of the Langley transonic tunnel in the open slotted test section. Results regarding test-section calibration, including flow uniformity, calibration, and angularity, model testing and boundary interference, and reduction of interference are provided.
Report presenting five fuels of boiling temperatures and several hydrocarbon types in a jet-propulsion annular combustor to determine the effect of fuel boiling temperature and paraffinic and aromatic hydrocarbon types on combustion efficiency and altitude operational limit. At the severe inlet-air condition, the highest combustion efficiencies were obtained with the paraffinic and aromatic fuels with low boiling temperatures were found to vary from 30 to 58 percent.
Report presenting a comparison of normal load factors measured during combat operations with those measured during an NACA flight program conducted with fully instrumented service airplanes in operational training. Results indicated that for an equal number of maneuvers, normal load factors obtained from the NACA program are greater than those obtained during combat when based on the service-limit load factor.
Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.
Memorandum presenting a force-test investigation to determine whether the static stability characteristics of a twisted and cambered 68.7 degree delta wing could be approximated by a plane wing of similar plan form with dihedral. Results regarding longitudinal characteristics and lateral characteristics are provided.
Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.
Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.
Memorandum presenting force tests that have been made of airplane configurations with a thin swept wing incorporating several wing-contour modifications forward of maximum thickness. Both longitudinal and lateral characteristics are provided.
Report presenting the design procedure and experimental test results for a range of impeller speeds for two vaned diffusers of 24 and 40 vanes. Both sets of vanes were designed to give approximately the same prescribed velocity distribution on the vane surfaces and were tested with the same impeller. Results regarding overall performance and the total-pressure-loss coefficient for both vanes are provided.
Report presenting a centrifugal impeller with a modified design procedure to reduce the velocity gradients existing along the hub from inlet to outlet. The modified impeller had better performance characteristics than the original at all speeds tested.
Report presenting an analysis of a number of free-flight transient responses resulting from small stabilizer movements obtained during testing of the Bell X-1 airplane to obtain its longitudinal stability characteristics. A comparison of flight data and model test data is also provided.
Memorandum presenting a brief account of the results of theoretical and experimental investigations of the flow fields behind lifting plane and cruciform wings. Particular attention is focused on wings of low aspect ratio.
Memorandum presenting an investigation of operation of a single-spool turbojet engine with variable exhaust-nozzle area over a range of altitudes at a constant flight Mach number. Data was obtained by subjecting the engine to approximate step disturbances in the independent variables, and the information necessary to effect a linearized first-order description of the engine's dynamic operation was obtained. Results regarding rotational speed, compressor-discharge pressure, turbine-discharge pressure, net thrust, and turbine-discharge temperature are provided.
Report of an investigation into the effect of leading-edge radius on the high-speed aerodynamic characteristics of a symmetrical, 9-percent-thick airfoil using three different airfoils at several Mach and Reynolds numbers. Information about the normal-force coefficients, drag coefficients, moment coefficients about the quarter chord, pressure-distribution diagrams, Schileren photographs, and a comparison with data obtained in other tunnels is included.
An investigation was conducted in the NACA Lewis altitude wind tunnel to determine the effect of compressor-outlet bleedoff on the performance of an axial-flow turbojet engine equipped with a variable-area exhaust nozzle. Results presented indicate the effect of compressor-outlet bleedoff on performance at altitudes of 25,000 and 40,000 feet and a flight Mach number of 0.53. Variation of performance with bleedoff flow is indicated for operation with fixed- and variable-area exhaust nozzles. Temperature and pressure losses through the bleedoff ducting system are also discussed.
Memorandum presenting the results of a theoretical investigation of the lateral response and stability characteristics of the X-3 research airplane (Douglas Model No. 499D). Included are time histories calculated by a computer showing the effect of various disturbances on the lateral response of the airplane with 0 degrees geometric dihedral and -5 degrees dihedral.
Report presenting results of a four-plane formation flight with twelve pull-up maneuvers in the form of plots of maximum load factor attained versus airplane position for three combinations of four F2H airplanes. The load factor was generally found to increase toward the end of the formation, and movements of the lead plane that are too sharp might cause excessive loads on the last plane in the formation.
Report presenting an investigation at subsonic, transonic, and supersonic speeds of the effect of lip shape on drag, pressure recovery, and mass flow of a nose-inlet air-induction system. Four lips of varying degrees of bluntness were tested on a fuselage model at a range of Mach numbers and angles of attack. Results regarding pressure recovery, net drag, and analysis are provided.
Report presenting a free-flight investigation to determine the effect of wing camber and twist at Mach numbers from 1.4 to 2.1 on the lift, drag, and longitudinal stability of a configuration with 52.5 degrees sweptback wing of aspect ratio 3, and inline tail surfaces. Results regarding drag, total normal force and pitching moment, and wash at the horizontal tail are provided.
Report presenting an investigation on canard airplane configurations in preference to a trailing-edge flap or tail control. Wide ranges in control plan form, size, and position and in wing plan form were found. Interference effects between the canard and other configuration components were not serious, and those that might be can be reduced by rearrangement of the vertical tail.
Memorandum presenting an investigation of the leading-edge extensions, a trailing-edge extension, and a fence on the static longitudinal stability of a wing-fuselage-tail combination with a wing with 35 degrees of sweepback and an aspect ratio of 4.5. The investigation involved the use of force measurements and tuft studies on stall progression. Results regarding a model with unmodified wing, the effect of leading-edge modifications, the effects of the fence, a summary of the effects of compressibility, and some remarks on flow separation are provided.
Report presenting an investigation at high subsonic speeds to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Testing was conducted at a range of angles of attack, propeller thrust coefficients, Mach numbers, and Reynolds numbers.
Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.
Memorandum presenting an inlet-type axial-flow compressor rotor with a hub-tip diameter ratio of 0.4 at the rotor leading edge, which was designed, fabricated, and experimentally investigated. The results of the investigation indicated that stages with inlet hub-tip ratios as low as 0.4 can be designed within known practical aerodynamic specifications to produce satisfactory values of stage pressure ratio and efficiency at high specific weight flows.
Memorandum presenting the detailed blade-element performance of a five-stage axial-flow compressor for analysis purposes as well as to provide a contribution to the growing body of information necessary for continuing improvement in designing compressors. Results regarding overall and stage performance, blade-element performance, rotor blade-element performance, stator blade-element performance, comparison with design, consideration of boundary-layer blockage effects, and solution of equilibrium equation are provided.
Memorandum presenting an investigation of the distortion removal performance and associated total-pressure-loss characteristics of several freely rotating fans, three single-stage and two double-stage freely rotating fans over a range of radial and circumferential distortions of from 0 to 20 percent at inlet annulus Mach numbers from 0.30 to about 0.60. Results regarding individual fan performance, comparison of fan distortion removal characteristics, and fan total-pressure loss and operating speed characteristics are provided.
Report presenting measurements of the damping in roll of cruciform triangular wings of aspect ratios 0.64, 1.28, and 2.31 at supersonic Mach numbers from 1.5 to 6.0. The models were launched from rifled guns and the time history of the model roll position in free flight was explored. Results regarding the comparison with theory, transonic effects, and comparison with results at other facilities are provided.
Memorandum presenting an experimental investigation to determine the flutter characteristics of several rectangular wings of variable aspect ratio at a range of Mach numbers. The wings were solid aluminum or steel and were 2, 4, and 6 percent thick. Results regarding the flutter at low and high angles of attack are provided.
Report presenting the performance increase resulting from the addition of fluorine to the oxygen-JP4 rocket propellant combination evaluated experimentally in a 1000-pound-thrust engine with 0, 30, and 70 percent of fluorine by weight in the oxidant. Maximum specific impulse values obtained were 259, 278, and 287 pound-seconds per pound, respectively, at a combustion pressure of 600 pounds per square inch absolute.
From Summary: "During a flight investigation of the lateral stability characteristics of a high-speed delta-wing airplane, violent cross-coupled lateral and longitudinal motions were encountered. The maneuver which produced these motions was an abrupt, rudder-fixed aileron roll performed at a Mach number of 0.75 at about 40,000 feet. The motions were characterized by extreme variations in angle of attack and angle of sideslip which caused the airplane to exceed the normal and transverse acceleration limitations."
Report presenting free-falling recoverable model tests conducted at transonic speeds on a model with a triangular wing of aspect ratio 2 and a 45 degree swept tail in the chord plane of the wing. Static- and dynamic-longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at several angles of attack.
Report presenting a flight investigation on a roll-stabilized ram-jet test vehicle over a range of Mach numbers from 2.3 to 2.7, a range of fuel-air ratio from 0.038 to 0.050, and an altitude range from 3,000 to 40,000 feet. Results regarding test conditions, engine performance, and roll autopilot performance are provided. The engines operated satisfactorily over the test time and the roll-control system operated satisfactorily at the beginning of testing.
Report presenting a flight investigation on a roll-stabilized ramjet test vehicle to determine engine performance over a range of Mach numbers, a range of fuel-air ratio, and an altitude range. Results regarding engine performance and roll autopilot performance are provided.
Report presenting flight tests to measure the directional stability of a fighter-type airplane over a range of Mach numbers. Testing occurred at two altitudes and used three vertical tails of varying aspect ratio or area.
Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting, free-floating fuel tanks attached to the wing tips. The results showed that the flight behavior of the configuration could be made satisfactory when sufficient restoring moment was supplied. Results regarding the flight behavior, rolling motions, motions of the bomber and attached tanks, and flight records for different gearing ratios are provided.
Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.
Report presenting an investigation of a model of the Chance Vought XF8U-1 airplane to determine the effect of spin-recovery rockets on the recovery characteristics of the model. The investigation also included tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. Results regarding yaw rockets, thrust-simulation rocket, and roll rockets are provided.
Memorandum presenting an investigation of a semispan-wing-fuselage model with a 60 degree delta wing with an aspect-ratio-8.2 blunt trailing-edge flap-type control in the 9- by 12-inch blowdown tunnel. Control hinge-moment and effectiveness characteristics were obtained over an angle-of-attack range of plus or minus 10 degrees at control deflections up to 90 degrees.
Report presenting an investigation in Langley tank no. 2 to determine the hydrodynamic characteristics of the Consolidated Vultee Skate 7 seaplane with twin hydro-skis suitable for use on water or snow. Results regarding the take-off stability in smooth and rough water, landing stability, spray characteristics, and resistance are provided.
Report presenting hydrodynamic planing lifts obtained in a free jet at speeds from 80 to 200 fps for four planing surfaces. The surfaces tested included a flat plate, a longitudinally curved model, a cylinder, and a hydro-ski with a complex-shaped bottom. Lift data was analyzed to show the effect of speed, planing-surface configuration, trim, and wetted-length-beam ratio at high speeds.
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