National Advisory Committee for Aeronautics (NACA) - 425 Matching Results

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Smoking Characteristics of Various Fuels as Determined by Open-Cup and Laboratory-Burner Smoke Tests

Description: Report discussing tests in a combustion chamber to obtain smoking characteristics data on a variety of hydrocarbon fuels. Details about the smoking tendencies and burning rates of the fuels in uncontrolled and controlled tests are provided.
Date: {1945-06, 1945-09}
Creator: Ebersole, Earl R. & Barnett, Henry C.
Partner: UNT Libraries Government Documents Department

A method for the calculation of external lift, moment, and pressure drag of slender open-nose bodies of revolution at supersonic speeds

Description: An approximate method is presented for the calculation of the external lift, moment, and pressure drag of slender open-nose bodies of revolution of supersonic speeds. The lift, moment, and pressure drag of a typical ram-jet body shape are calculated at Mach numbers 1.45, 1.60, 1.75, and 3.00; and the lift and moment results are compared with available experimental data. The agreement of the calculated lift and moment data with the experimental data is excellent. The pressure-drag comparison was not presented because of the uncertainty of the amount of skin-friction drag present in the experimental results.
Date: December 29, 1945
Creator: Brown, Clinton E. & Parker, Hermon M.
Partner: UNT Libraries Government Documents Department

Bending-torsion flutter calculations modified by subsonic compressibility corrections

Description: From Summary: "A number of calculations of bending-torsion wing flutter are made at two Mach numbers, m=0 (incompressible case) and m=0.7, and results are compared. The air forces employed for the case of m=0.7 are based on Frazer's recalculation of Possio's results, which are derived on the assumption of small disturbances to the main flow. For ordinary wings of normal density and of low bending frequency in comparison with torsion frequency, the compressibility correction to the flutter speed appears to be of the order of a few percent; whereas the correction to flutter speed for high-density wing sections, such as propeller sections, and to the wing-divergence speed in general, may be based on a rule using the (1 - m(2))1/4 factor and, for m=0.7, represents a decrease of the order of 17 percent."
Date: December 18, 1945
Creator: Garrick, I. E.
Partner: UNT Libraries Government Documents Department

Relation between spark-ignition engine knock, detonation waves, and autoignition as shown by high-speed photography

Description: "A critical review of literature bearing on the autoignition and detonation-wave theories of spark-ignition engine knock and on the nature of gas vibrations associated with combustion and knock results in the conclusion that neither the autoignition theory nor the detonation-wave theory is an adequate explanation of spark-ignition engine knock. A knock theory is proposed, combining the autoignition and detonation-wave theories, which introduces the idea that the detonation wave develops in autoignited or after-burning gases, and ascribes comparatively low-pitched heavy knocks to autoignition but high-pitched pinging knocks to detonation waves with the possibility of combinations of the two types of knocks" (p. 317).
Date: December 5, 1945
Creator: Miller, Cearcy D.
Partner: UNT Libraries Government Documents Department

Analysis of V-G Records From the SNJ-4 Airplane

Description: Report discusses an attempt to adapt a method of analysis of V-G data to predict the occurrences of large values of airspeed and acceleration from an SNJ-4 airplane; the data are presented as "flight envelopes". The flight envelopes "predict that, on average, in a stated number of flight hours, one airspeed, one positive acceleration, and one negative acceleration will exceed the envelope with equal probability of the accelerations being experienced at any airspeed" (from Discussion). The analysis method shows promise for predicting flight loads and speeds for airplanes on which loads due to maneuvers predominate.
Date: December 1945
Creator: Wilkerson, M. & Bennett, S. A.
Partner: UNT Libraries Government Documents Department

Calculations of Economy of 18-Cylinder Radial Aircraft Engine With Exhaust-Gas Turbine Geared to the Crankshaft at Cruising Speed

Description: Report presenting calculations based on dynamometer test-stand data on an 18-cylinder radial engine made to determine the improvement in fuel consumption that can be obtained by gearing an exhaust-gas turbine to the engine crankshaft in order to increase the engine shaft work.
Date: December 1945
Creator: Hannum, Richard W.
Partner: UNT Libraries Government Documents Department

Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination 1: Performance of a Highly Supercharged Compression-Ignition Engine

Description: From Summary: "Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm."
Date: December 1945
Creator: Sanders, J. C. & Mendelson, Alexander
Partner: UNT Libraries Government Documents Department

Column Strength of Extruded Magnesium Alloys AM-C58S and AM-C58S-T5

Description: "Tests have previously been made to determine the column strength of magnesium alloy AM-C58S-T5 extruded rod, but these few data were not considered a satisfactorily wide basis for establishing a general formula for the column strength of this alloy. It was therefore decided to make additional tests on a number of extruded sections of magnesium alloy AM-C58S-T5 with some tests on AM-C58S for comparison" (p. 1).
Date: December 1945
Creator: Leary, J. R. & Holt, Marshall
Partner: UNT Libraries Government Documents Department

The effect of concentrated loads on flexible rings in circular shells

Description: Report presenting a method of making strain measurements on a series of circular cylinders with reinforcing rings, subjected to concentrated loads, in which the bending stiffness of the rings was varied systematically over a wide range. Results regarding the general remarks, bending-moment coefficient, and skin shear coefficients are provided.
Date: December 1945
Creator: Kuhn, Paul; Duberg, John E. & Griffith, George E.
Partner: UNT Libraries Government Documents Department

Effect of Propeller-Axis Angle of Attack on Thrust Distribution Over the Propeller Disk in Relation to Wake-Survey Measurement of Thrust

Description: "Tests were made to investigate the variation of thrust distribution over the propeller disk with angle of pitch of the propeller thrust axis and to determine the disposition and the minimum number of rakes necessary to measure the propeller thrust. The tests were made at a low Mach number for a low and a high blade angle with the propeller operating at three small angles of pitch, and some of the tests were repeated at a higher Mach number. The data obtained show that, for small angles of pitch, large changes occur in the energy distribution in the wake which prohibit the use of a single survey rake for thrust measurement in flight tests and limit the use of a single rake in wind-tunnel tests" (p. 1).
Date: December 1945
Creator: Pendley, Robert E.
Partner: UNT Libraries Government Documents Department

Effects of Wing and Nacelle Modifications on Drag and Wake Characteristics of a Bomber-Type Airplane Model

Description: Report presenting an investigation of a model of a large four-engine bomber to determine the effects of several wing and nacelle modifications on drag characteristics and airflow characteristics at the tail. Leading-edge gloves, trailing-edge extensions, and modified nacelle afterbodies were all tested. Results regarding flow characteristics at the wing during flight and at the landing condition, flow characteristics at the tail, and longitudinal stability characteristics are provided.
Date: December 1945
Creator: Neely, Robert H.; Fairbanks, Richard W. & Conner, D. William
Partner: UNT Libraries Government Documents Department

Fatigue Strength of Flush-Riveted Joints for Aircraft Manufactured by Various Riveting Methods

Description: Report presenting the results of an investigation to determine the fatigue strength of flush-riveted joints manufactured by different riveting methods. Tests were made on a direct stress fatigue machine at room temperature. The results showed that the fatigue strength of the joints was directly affected by the method of riveting used.
Date: December 1945
Creator: Maney, G. A. & Wyly, L. T.
Partner: UNT Libraries Government Documents Department

A flight investigation of NACA aileron modifications for the improvement of the lateral control characteristics of a high-speed fighter airplane

Description: Report presenting a flight investigation to improve the lateral control of a high-speed fighter airplane. Testing occurred with the original ailerons and a set of modified ailerons, which consisted of an increased balance chord and increased nose radius. The modified ailerons appear to offer a solution to the problem of aileron overbalance and oscillation in high-speed dives.
Date: December 1945
Creator: Williams, Walter C.
Partner: UNT Libraries Government Documents Department

Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 1: Description of Setup and Testing Technique

Description: Report discussing icing and de-icing of the carburetor and supercharger inlet of typical aircraft engine induction systems. A description of the systems used to control and simulate different conditions is provided.
Date: December 1945
Creator: Mulholland, Donald R.; Rollin, Vern G. & Galvin, Herman B.
Partner: UNT Libraries Government Documents Department

Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 2: Determination of the Limiting-Icing Conditions

Description: "The carburetor and engine-stage supercharger assembly of a fighter aircraft were laboratory-tested to determine the icing characteristics of the induction system under three simulated engine power conditions with varying carburetor-air temperature, relative humidity, simulated-rain injection, rain and fuel temperature, fuel-air ratio, and fuel of different distillation characteristics" (p. 1).
Date: December 1945
Creator: Essex, Henry A.; Keith, Wayne C. & Mulholland, Donald R.
Partner: UNT Libraries Government Documents Department

Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 3: Heated Air as a Means of De-Icing the Carburetor and Supercharger Inlet Elbow

Description: Report discussing the use of a twin-barrel injection carburetor and a supercharger inlet elbow to establish the relation between wet- and dry-bulb temperatures of the de-icing air and time required to recover from air-flow loss due to icing. The tests were performed at several power conditions, icing conditions, temperatures, and dry and humidified air. De-icing time was found to be a function of the nature of the ice formation and of the wet-bulb temperature of the de-icing air.
Date: December 1945
Creator: Lyons, Richard E. & Coles, Willard D.
Partner: UNT Libraries Government Documents Department

Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 5: Effect of Injection of Water-Fuel Mixtures and Water-Ethanol-Fuel Mixtures on the Icing Characteristics

Description: Report discussing the effects of internal coolants injected with fuel on the icing characteristics of a twin-barrel injection carburetor mounted on an engine-stage supercharger assembly. The tests were made at conditions that simulated war emergency power and at a variety of water-fuel ratios, carburetor-air temperatures, and carburetor-air relative humidities.
Date: December 1945
Creator: Renner, Clark E.
Partner: UNT Libraries Government Documents Department

A Metallurgical Investigation of a Large Forged Disc of Low-Carbon N-155 Alloy

Description: Report presenting a research program to ascertain the properties of promising heat-resistant alloys in the form of the large forgings required. The properties of a large disc of Low-Carbon N155 alloy in the hot-forged and stress-relieved condition have been determined by means of stress-rupture and creep tests for time periods up to 2000 hours at 1200, 1350, and 1500 degrees Fahrenheit. Results regarding hardness, short-time tensile properties, Charpy impact strength, rupture test characteristics, time-deformation characteristics, creep strengths, and stability characteristics are provided.
Date: December 1945
Creator: Freeman, J. W. & Cross, H. C.
Partner: UNT Libraries Government Documents Department

A Method for the Determination of Aromatics in Hydrocarbon Mixtures

Description: Bulletin discusses a method to estimate aromatic hydrocarbons in hydrocarbon mixtures, which is important for determining the percentage of aromatics in fuel blends. The method was tested with nine base stocks at several levels of aromatics concentration and the maximum level of error was found to be about 0.5 percent. The speed and simplicity of the testing is emphasized.
Date: December 1945
Creator: Hipsher, Harold F.
Partner: UNT Libraries Government Documents Department

Performance tests of wire strain gages 3: calibrations at high tensile strains

Description: Report presenting results of calibration in axial tension over the strain range 0 to 0.03 are presented for 15 types of single element, multistrand wire strain gages. Considerable nonlinearity was observed at strains between 0.0025 and 0.006. Fifty-eight percent of the gages failed by breaking of the strain-sensitive wire at strains less than 0.03.
Date: December 1945
Creator: Campbell, William R.
Partner: UNT Libraries Government Documents Department

Piston Heat-Transfer Coefficients Across an Oil Film in a Smooth-Walled Piston Reciprocating-Sleeve Apparatus

Description: Report presenting tests conducted with a heat-transfer apparatus that simulates the piston-cylinder-wall relation by means of a stationary, electrically heated, smooth-walled aluminum piston and a reciprocating steel sleeve separated by an oil film. Results regarding heat balance, temperature distribution, heat input, speed, average sleeve temperature, side thrust, piston-clearance oil-supply rate, and specific variable correlation are provided.
Date: December 1945
Creator: Manganiello, Eugene J. & Bogart, Donald
Partner: UNT Libraries Government Documents Department