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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
 Collection: National Advisory Committee for Aeronautics Collection
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/
Estimates of the vertical-tail loads of a Bell P-63A-1 airplane (AAF No. 42-68889) in accelerated rolling maneuvers based on flight tests with two vertical-tail arrangements
No Description digital.library.unt.edu/ark:/67531/metadc61501/
Estimation of F-3 and F-4 knock-limited performance ratings for ternary and quaternary blends containing triptane or other high-antiknock aviation-fuel blending agents
No Description digital.library.unt.edu/ark:/67531/metadc62293/
Estimation of the performance and longitudinal stability and control of a lifting-body type of cargo airplane from tests of simplified models
No Description digital.library.unt.edu/ark:/67531/metadc61179/
An evaluation of the knock-limited performance of triptane
No Description digital.library.unt.edu/ark:/67531/metadc62312/
An Experimental Investigation of Flow Conditions in the Vicinity of an NACA D(Sub S)-Type Cowling
Data are presented of the flow conditions in the vicinity of an NACA D sub S -type cowling. Tests were made of a 1/2 scale-nacelle model at inlet-velocity ratios ranging from 0.23 to 1.02 and angles of attack from 6 deg to 10 deg. The velocity and direction of flow in the vertical plane of symmetry of the cowling were determined from orifices and tufts installed on a board aligned with the flow. Diagrams showing velocity ratio contours and lines of constant flow angles are given. digital.library.unt.edu/ark:/67531/metadc62102/
An Experimental Investigation of NACA Submerged-Duct Entrances
The results of an investigation of submerged-duct entrances are presented. It is shown that this type of entrance possesses the following characteristics: 1) very high-critical-compressibility speeds throughout the range of high-speed inlet velocity ratios; 2) very low pressure losses for the air entering the duct at all inlet-velocity ratios; and, 3) low external drag. These characteristics are obtained by the proper shaping of the contour of the upstream approach to the submerged inlets and by proper alignment of the duct lip. Design data are presented and the application of these data to a specific high-speed fighter-airplane design is discussed. digital.library.unt.edu/ark:/67531/metadc65007/
F-3 and F-4 engine tests of several high-antiknock components of aviation fuel
No Description digital.library.unt.edu/ark:/67531/metadc62363/
Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines I : determination of cooling characteristics of flight engine
No Description digital.library.unt.edu/ark:/67531/metadc62522/
Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines II : flight knock data and comparison of fuel knock limits with engine cooling limits in flight
No Description digital.library.unt.edu/ark:/67531/metadc62523/
Flight and test-stand investigation of high-performance fuels in modified double-row radial air-cooled engines I : determination of the cooling characteristics of the flight engine
No Description digital.library.unt.edu/ark:/67531/metadc62537/
Flight and test-stand investigation of high-performance fuels in modified double-row radial air-cooled engines II : flight knock data and comparison of fuel knock limits with engine cooling limits in flight
No Description digital.library.unt.edu/ark:/67531/metadc62538/
Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines III: Knock-Limited Performance of 33-R as Compared with a Triptane Blend and 28-R in Flight
A comparison has been made in flight of the antiknock characteristics of 33-R fuel with that of 28-R and a triptane blent. The knock-limited performance of the three fuels - 33-R, a blend of 80 percent 28-R plus 20 percent triptane (leaded to 4.5 ml TEL/gal), and 28-R - was investigated in two modified 14-cylinder double-row radial air-cooled engines. Tests were conducted on the engines as installed in the left inboard nacelle of an airplane. A carburetor-air temperature of approximately 85 deg F was maintained. The conditions covered at an engine speed of 2250 rpm were high and low blower ratios and spark advances of 25 deg and 32 deg B.T.C. For an engine speed of 1800 rpm only the high-blower condition was investigated for both 25 deg and 32 deg spark advances. For the conditions investigated the difference between 33-R and the triptane blend was found to be slight; the performance of 33-R fuel, however, was slightly higher than that of the triptane blend in the lean region. The knock-limited power obtained with the 33-R fuel was from 14 to 28 percent higher than that of the 28-R fuel for the entire range of test conditions; the greatest improvement was shown in the lean region. digital.library.unt.edu/ark:/67531/metadc62539/
Flight investigation of factors affecting the carburetor ram and nacelle drag of an A-26B airplane
No Description digital.library.unt.edu/ark:/67531/metadc62684/
Flight investigation of modifications to improve the elevator control-force characteristics of the Curtiss SB2C-10 airplane in maneuvers
No Description digital.library.unt.edu/ark:/67531/metadc61602/
A Flight Investigation of the Ice-Prevention Requirements of the United States Naval K-Type Airship
No Description digital.library.unt.edu/ark:/67531/metadc62474/
Flight Investigation to Improve the Dynamic Longitudinal Stability and Control-Feel Characteristics of the P-63A-1 Airplane (AAF No. 42-68889) with Closely Balanced Experimental Elevators
Results of flight tests of a control-feel aid presented. This device consisted of a spring and dashpot connected in series between the control stick and airplane structure. The device was tested in combination with an experimental elevator and bobweight which had given unsatisfactory dynamic stability and control-feel characteristics in previous tests. The control-feel aid effected marked improvement in both the control-feel characteristics and the control-feel dynamic longitudinal stability of the airplane. digital.library.unt.edu/ark:/67531/metadc61127/
Flight measurements by various methods of the drag characteristics of the XP-51 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61740/
Flight measurements of the effect on elevator stick forces of stabilizer incidence and elevator rib spacing on the P-63A-1BE series airplane
No Description digital.library.unt.edu/ark:/67531/metadc62617/
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) I : longitudinal stability and control
No Description digital.library.unt.edu/ark:/67531/metadc61068/
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) II : lateral and directional stability and control
No Description digital.library.unt.edu/ark:/67531/metadc61071/