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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
 Collection: National Advisory Committee for Aeronautics Collection
Accelerations and bottom pressures measured on a B-24D airplane in a ditching test
No Description digital.library.unt.edu/ark:/67531/metadc61135/
Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage
No Description digital.library.unt.edu/ark:/67531/metadc61201/
Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels
Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections of the XF-12 airplane, were tested in the Langley two-dimensional low-turbulence tunnels to obtain their aerodynamic characteristics. Lift characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, 9,000,000, and 14,000,000, whereas drag characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, and 9,000,000. Pressure distributions were obtained for one of the root sections for several angles of attack at a Reynolds number of 2,600,000. Comparison of the root section that appeared best from the tests with the corresponding NACA 65-series section shows the Republic section has a higher maximum lift and higher calculated critical speeds, but a higher minimum drag. In addition, with standard roughness applied to the leading edge, the maximum lift of the Republic airfoil is lower than that of the NACA airfoil. Comparison of the Republic tip section with the corresponding NACA 65-series section shows the Republic airfoil has a lower maximum lift and a higher minimum drag than the NACA airfoil. The calculated critical speeds of the Republic section are slightly higher than those of the NACA section. digital.library.unt.edu/ark:/67531/metadc64938/
Aerodynamic characteristics of several modifications of a 0.45-scale model of the vertical tail of the Curtiss XP-62 airplane
No Description digital.library.unt.edu/ark:/67531/metadc62683/
Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap
No Description digital.library.unt.edu/ark:/67531/metadc61451/
Aerodynamic tests of an NACA 66(215)-116, a=0.6 airfoil with a 0.25c slotted flap for the Fleetwings XA-39 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61411/
Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane
No Description digital.library.unt.edu/ark:/67531/metadc62050/
Air-flow and performance characteristics of engine-stage supercharger of a double-row radial aircraft engine II : effect of design variables
No Description digital.library.unt.edu/ark:/67531/metadc62038/
Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I : effect of operating variables
No Description digital.library.unt.edu/ark:/67531/metadc62036/
Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter
No Description digital.library.unt.edu/ark:/67531/metadc61183/
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/
Ditching behavior of military airplanes as affected by ditching aids
No Description digital.library.unt.edu/ark:/67531/metadc61115/
Ditching tests of a 1/8-scale model of the Navy SB2C-1 airplane (Army A-25) in Langley tank number 2 and on an outdoor catapult
No Description digital.library.unt.edu/ark:/67531/metadc62628/
Ditching tests with 1/16-size models of the Army B-17 airplane in Langley tank number 2 and on an outdoor catapult
No Description digital.library.unt.edu/ark:/67531/metadc62626/
Ditching tests with a 1/10-size model of the Army A-20A airplane in Langley tank no.2 and on an outdoor catapult
No Description digital.library.unt.edu/ark:/67531/metadc62621/
Ditching tests with a 1/11-size model of the Army B-25 airplane in NACA tank number 2 and on an outdoor catapult
No Description digital.library.unt.edu/ark:/67531/metadc62629/
Ditching tests with a 1/16-size dynamic model of the Army B-24 airplane in Langley tank number 2 and on an outdoor catapult
No Description digital.library.unt.edu/ark:/67531/metadc62625/
Economy of internally cooling only the overheated cylinders of aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc61959/
The effect of a low-loss air valve on performance of a 22-inch-diameter pulse-jet engine
No Description digital.library.unt.edu/ark:/67531/metadc62467/
The effect of afterbody length of the hydrodynamic stabilit y of a dynamic model of a flying boat : Langley tank model 134
No Description digital.library.unt.edu/ark:/67531/metadc62685/
Effect of blade loading of the climb and high-speed performance of a three-blade Hamilton standard no. 6507A-2 propeller on a Republic P-47D airplane
No Description digital.library.unt.edu/ark:/67531/metadc62616/
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/
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