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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
 Collection: National Advisory Committee for Aeronautics Collection
Analysis and correlation of data obtained by six laboratories on fuel-vapor loss from fuel tanks during simulated flight
No Description digital.library.unt.edu/ark:/67531/metadc62280/
An analysis of the indications of the University of Chicago airborne turbulence indicator in gusty air
No Description digital.library.unt.edu/ark:/67531/metadc62668/
Analysis of V-G Records from the SNB-1 Airplane
Availability data obtained on SNB-1 trainer-class airplanes were analyzed and results presented as flight envelopes which predict occurrences of large values of air speed and acceleration. Comparison is made with SNJ-4 trainer-class airplane data analyzed by the same method. It is concluded that flight envelopes are satisfactory; that the two types show large differences in flight loads and speeds experience; and that SNB-1 will seldom, if ever, exceed design limit load factor and restricted speed, which SNJ-4 can be expected to exceed design-limit load factor and restricted speed in a very small number of flight hours. digital.library.unt.edu/ark:/67531/metadc62643/
Analysis of V-G records from the SNJ-4 airplane
No Description digital.library.unt.edu/ark:/67531/metadc62613/
Analytical investigation of the stability of an F8F dropping model with automatic stabilization
No Description digital.library.unt.edu/ark:/67531/metadc61655/
Attainment of a straight-line trajectory for a preset guided missile with special reference to effect of wind or target motion
No Description digital.library.unt.edu/ark:/67531/metadc62433/
Bending and shear stresses developed by the instantaneous arrest of the root of a cantilever beam with a mass at its tip
No Description digital.library.unt.edu/ark:/67531/metadc62215/
Calculation of the aileron and elevator stick forces and rudder pedal forces for the Bell XP-83 airplane (project MX-511) in spins
No Description digital.library.unt.edu/ark:/67531/metadc61570/
Calibrations of service pitot tubes in the Langley 24-inch high-speed tunnel
No Description digital.library.unt.edu/ark:/67531/metadc62408/
Characteristics of several single- and dual-rotating propellers in negative thrust
No Description digital.library.unt.edu/ark:/67531/metadc62187/
Characteristics of the BMW 801D2 automatic engine control as determined from bench tests
No Description digital.library.unt.edu/ark:/67531/metadc62109/
Charts showing stability and control characteristics of airplanes in flight
No Description digital.library.unt.edu/ark:/67531/metadc60953/
Comparison of predicted and actual control-fixed stability and control characteristics of a Douglas A-26B airplane
No Description digital.library.unt.edu/ark:/67531/metadc61056/
Comparison of the knock-limited performance of triptane with 23 other purified hydrocarbons
No Description digital.library.unt.edu/ark:/67531/metadc62298/
Control of cylinder temperatures by thermostatically operated internal-coolant valves
No Description digital.library.unt.edu/ark:/67531/metadc61968/
A cooling correlation equation for a double-row radial engine based on the temperature of the exhaust-valve seat
No Description digital.library.unt.edu/ark:/67531/metadc62018/
Cooling of a double-row radial engine by water injection to the individual cylinders
No Description digital.library.unt.edu/ark:/67531/metadc62015/
Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades
An analysis of rim cooling, which cools the blade by condition alone, was conducted. Gas temperatures ranged from 1300 degrees to 1900 degrees F and rim temperatures from 0 degrees to 1000 degrees F below gas temperatures. Results show that gas temperature increases up to 200 degrees F are permissible provided that the blades are cooled by 400 degrees to 500 degrees F below the gas temperature. Relatively small amounts of blade cooling, at constant gas temperature, give large increases in blade life. Dependence of rim cooling on heat-transfer coefficient, blade dimensions, and thermal conductivity is determined by a single parameter. digital.library.unt.edu/ark:/67531/metadc65597/
Correlation of engine-cooling data
No Description digital.library.unt.edu/ark:/67531/metadc61958/
Correlation of mixture temperature data obtained from bare intake-manifold thermocouples
A relatively simple equation has been found to express with fair accuracy, variation in manifold-charge temperature with charge in engine operating conditions. This equation and associated curves have been checked by multi cylinder-engine data, both test stand and flight, over a wide range of operating conditions. Average mixture temperatures, predicted by the equations of this report, agree reasonably well with results within the same range of carburetor-air temperatures from laboratories and test stands other than the NACA. digital.library.unt.edu/ark:/67531/metadc61878/
Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine I : Cooling Characteristics
Variable charge-air flow, cooling-air pressure drop, and fuel-air ration investigations were conducted to determine the cooling characteristics of a full-scale air-cooled single cylinder on a CUE setup. The data are compared with similar data that were available for the same model multicylinder engine tested in flight in a four-engine airplane. The cylinder-head cooling correlations were the same for both the single-cylinder and the flight engine. The cooling correlations for the barrels differed slightly in that the barrel of the single-cylinder engine runs cooler than the barrel of te flight engine for the same head temperatures and engine conditions. digital.library.unt.edu/ark:/67531/metadc62546/
Correlation of the characteristics of single-cylinder and flight engines in tests of high-performance fuels in an air-cooled engine II : knock-limited charge-air flow and cylinder temperatures
An investigation was conducted to correlate the knock limited performance of flight and single-cylinder engines under a variety of operating conditions. digital.library.unt.edu/ark:/67531/metadc62547/
Correlation of wind-tunnel predictions with flight tests of a twin-engine airplane I : longitudinal-stability and -control characteristics
No Description digital.library.unt.edu/ark:/67531/metadc61036/
Correlation of wind-tunnel predictions with flight tests of a twin-engine patrol airplane II : lateral- and directional-stability and control characteristics
No Description digital.library.unt.edu/ark:/67531/metadc61041/
Correlation Tests of the Ditching Behavior of an Army B-24D Airplane and a 1/16-Size Model
Behaviors of both model and full-scale airplanes were ascertained by making visual observations, by recording time histories of decelerations, and by taking motion picture records of ditchings. Results are presented in form of sequence photographs and time-history curves for attitudes, vertical and horizontal displacements, and longitudinal decelerations. Time-history curves for attitudes and horizontal and vertical displacements for model and full-scale tests were in agreement; maximum longitudinal decelerations for both ditchings did not occur at same part of run; full-scale maximum deceleration was 50 percent greater. digital.library.unt.edu/ark:/67531/metadc62618/
Determination of air-consumption parameters for two radial aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc61869/
The effect of compression ratio on knock limits of high-performance fuels in a CFR engine I : blends of triptane and 28-R fuel
No Description digital.library.unt.edu/ark:/67531/metadc62519/
The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine II : Blends of 2,2,3-Trimethylpentane with 28-R
The knock-limited performance of blends of 0,50; and 100 percent by volume of 2,2,3-trimethylpentane in 28-R fuel determined with a modified F-4 engine at three sets of conditions varying from severe to mild at each of three compression ratios (6.0, 8.0, and 10.0). A comparison of the knock-limited performance of 2,2,3-trimethylpentane with that of triptane (2,2,3-trimethylbutane) is included. The knock-Limited performance of 2,2,3-trimethylpontane was usually more sensitive to either compression ratio or inlet-air temperature than 28-R fuel, but the ratio of the knock-limited indicated mean effective pressure of a given blend containing 2,2,3-trimethypentane and 28-R to the indicated mean effective pressure of 28-R alone was not greatly affected by compression ratio if the engine operating conditions were mild. Although 2,2,3-trimethylpentane in general had a lower knock-limited performance than triptane, the characteristics of the two fuels were somewhat similar. digital.library.unt.edu/ark:/67531/metadc62525/
The effect of compression ratio on knock limits of high-performance fuels in a CFR engine III : blends of 2,3-dimethylpentane with 28-R
No Description digital.library.unt.edu/ark:/67531/metadc62381/
Effect of engine-operating variables and internal coolants on spark-advance requirements of a liquid-cooled cylinder
No Description digital.library.unt.edu/ark:/67531/metadc61914/
The effect of ethylene dibromide on the knock-limited performance of leaded and nonleaded S reference fuel
No Description digital.library.unt.edu/ark:/67531/metadc62310/
Effect of fuel volatility and mixture temperature on the knocking characteristics of a liquid-cooled single-cylinder test engine
No Description digital.library.unt.edu/ark:/67531/metadc62535/
The effect of high-resistance ignition cable on the erosion of spark-plug electrodes
No Description digital.library.unt.edu/ark:/67531/metadc62091/
The effect of increase in combustion-air inlet temperature from 80 to 130 F on the sea-level performance of a 22-inch-diameter pulse-jet engine
No Description digital.library.unt.edu/ark:/67531/metadc62549/
Effect of internal coolants on the knock-limited performance of an Allison V-1710-99 engine with a compression ratio of 6.0
No Description digital.library.unt.edu/ark:/67531/metadc61974/
The effect of liquid and ice particles on the erosion of a supercharger-inlet cover and diffuser vanes
No Description digital.library.unt.edu/ark:/67531/metadc62087/
Effect of Mach and Reynolds numbers on the maximum lift coefficient obtainable in gradual and abrupt stalls of a pursuit airplane equipped with a low-drag wing
No Description digital.library.unt.edu/ark:/67531/metadc61288/
The effect of Mach number on the aerodynamic characteristics of a single-engine pursuit airplane as determined from tests of a 1/3-scale model
No Description digital.library.unt.edu/ark:/67531/metadc61229/
Effect of Maximum Cruise-Power Operation at Ultra-Lean Mixture and Increased Spark Advance on the Mechanical Condition of Cylinder Components
A continuous 50-hour test was conducted to determine the effect of maximum cruise-power operation at ultra-lean fuel-air mixture and increased spark advance on the mechanical conditions of cylinder components. The test was conducted on a nine-cylinder air-cooled radial engine at the following conditions:brake horsepower, 750; engine speed, 1900 rpm; brake mean effective pressure, 172 pounds per square inch; fuel-air ratio, 0.052; spark advance, 30 deg B.T.C.; and maximum rear-spark-plug-bushing temperature, 400 F. In addition to the data on corrosion and wear, data are presented and briefly discussed on the effect of engine operation at the conditions of this test on economy, knock, preignition, and mixture distribution. Cylinder, piston, and piston-ring wear was small and all cylinder component were in good condition at the conclusion of the 50-hour test except that all exhaust-valve guides were bellmouthed beyond the Army's specified limit and one exhaust-valve face was lightly burned. It is improbable that the light burning in one spot of the valve face would have progressed further because the burn was filled with a hard deposit so that the valve face formed an unbroken seal and the mating seat showed no evidence of burning. The bellmouthing of the exhaust-valve guides is believed to have been a result of the heavy carbon and lead-oxide deposits, which were present on the head end of the guided length of the exhaust-valve stem. Engine operational the conditions of this test was shown to result In a fuel saving of 16.8 percent on a cooled-power basis as compared with operation at the conditions recommended for this engine by the Army Air Forces for the same power. digital.library.unt.edu/ark:/67531/metadc61884/
The effect of modified baffles and auxiliary-cooling ducts on the cooling of a double-row radial engine
No Description digital.library.unt.edu/ark:/67531/metadc62016/
Effect of NACA injection impeller and ducted head baffles on flight cooling performance of double-row radial engine in four-engine heavy bomber
No Description digital.library.unt.edu/ark:/67531/metadc62011/
The effect of six aromatic amines on the preignition-limited performance of 28-R aviation fuel in a CFR engine
No Description digital.library.unt.edu/ark:/67531/metadc62299/
The effect of some design parameters on ditching characteristics
No Description digital.library.unt.edu/ark:/67531/metadc60888/
Effect of the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger for thermal ice prevention
No Description digital.library.unt.edu/ark:/67531/metadc279594/
The effect of the skis on the power-off stability characteristics of a twin-engine cargo airplane
No Description digital.library.unt.edu/ark:/67531/metadc61063/
The effect of valve clearance on knock-limited performance and engine cooling
No Description digital.library.unt.edu/ark:/67531/metadc61879/
Effect of Water-Alcohol Injection and Maximum Economy Spark Advance on Knock-Limited Performance and Fuel Economy of a Large Air-Cooled Cylinder
An investigation was conducted to determine the effect of a coolant solution of 25 percent ethyl alcohol, 25 percent methyl alcohol, and 50 percent water by volume and maximum-economy spark advance on knock-limited performance and fuel economy of a large air-cooled cylinder. The knock-limited performance of the cylinder at engine speeds of 2100 and 2500 rpm was determined for coolant-fuel ratios of 0.0, 0.2, and 0.4. The effect of water-alcohol injection on fuel economy was determined in constant charge-air flow tests. The tests were conducted at a spark advance of 20 deg B.T.C. and maximum-economy spark advance. digital.library.unt.edu/ark:/67531/metadc62540/
Efficiency of a radial-flow exhaust-gas turbosupercharger turbine with a 12.75-inch tip diameter
No Description digital.library.unt.edu/ark:/67531/metadc61860/
Endurance tests of a 22-inch-diameter pulse-jet engine with a neoprene-coated valve grid
No Description digital.library.unt.edu/ark:/67531/metadc62544/
An estimate of the effect of engine supercharging on the take-off thrust of a typical helicopter at different altitudes and temperatures
No Description digital.library.unt.edu/ark:/67531/metadc61867/
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