Search Results

Design charts for cross-flow tubular intercoolers charge-through-tube type

Description: Report presenting equations relating the various dimensions, air weight flow, and performance of a cross-flow tubular intercooler in which the charge flows through and the cooling air across the tubes. A method of determining and presenting the performance of a given intercooler at various operating conditions is indicated. Results regarding the cooling effectiveness equation, effect of primary intercooler variables, design charts, effect of tube arrangement on intercooler characteristics, and performance charts are provided.
Date: July 1941
Creator: Reuter, J. George & Valerino, Michael F.
Partner: UNT Libraries Government Documents Department

An Electron and X-Ray Diffraction Investigation of Surface Changes on Nitrided-Steel Piston Rings During Engine Operation in Nitrided-Steel Cylinders Barrels

Description: Report presenting an examination of new and used nitrided-steel piston rings by electron and X-ray diffraction in a study of the surface changes produced during engine operation. Both new and used rings, examined after degreasing, gave an electron-diffraction pattern consisting of diffuse bands: those from used rings fell at the usual positions of the bands from polished metal surfaces.
Date: March 1945
Creator: Good, J. N. & Brockway, L. O.
Partner: UNT Libraries Government Documents Department

Design charts for cross-flow tubular intercoolers charge-across-tube type

Description: Report presenting equations relating the various dimensions, air mass flow, and performance of a cross-flow tubular intercooler in which the charge flows across and the cooling air through the tubes. Design charts are presented from which the intercooler design characteristics and performance can be quickly determined.
Date: January 1941
Creator: Reuter, J. George & Valerino, Michael F.
Partner: UNT Libraries Government Documents Department

A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine 1

Description: Report presenting a method of correlating the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels. Knock-limited performance tests of several fuels were run to check the method.
Date: May 1945
Creator: Evvard, John C. & Branstetter, J. Robert
Partner: UNT Libraries Government Documents Department

Calibrations of pitot-static tubes at high speeds

Description: Report presenting the calibrations of three types of service pitot-static tubes over an approximate range of speeds of 150 to 600 miles per hour. The calibrations indicated a need for a pitot-static tube with greater accuracy, especially at higher speeds. Results regarding the service tubes, Prandtl tube, Eigh-speed tube, and a comparison of the tubes are provided.
Date: July 1942
Creator: Hensley, Reece V.
Partner: UNT Libraries Government Documents Department

A Metallurgical Investigation of a Large Forged Disc of 19-9 DL Alloy

Description: Report presenting an investigation of the properties of a 20-inch diameter by 3.25 inch disc of 19-9 DL alloy in the as-forged and stress-relieved condition. Results regarding the hardness survey, short-time tensile properties, rupture test characteristics, time for deformation characteristics under stress, creep strengths, and stability characteristics are provided.
Date: March 1945
Creator: Freeman, J. W.; Reynolds, E. E. & White, A. E.
Partner: UNT Libraries Government Documents Department

Observations of the Improvement in Vision Brought About by the Application of a Rain-Repellent Lacquer on an Airplane Windshield

Description: "A rain-repellent lacquer was submitted to the National Advisory Committee for Aeronautics by Captain K.H. Kalberer, of Lorr Laboratories, and preliminary tests and observations have been made to determine its value in improving the vision through an airplane windshield during rain. The tests and observations were carried out at Ames Aeronautical Laboratory, Moffett Field, California, over a period of about a week. The results are reported herein" (p. 2).
Date: May 1942
Creator: McAvoy, William H. & Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department

Supercharged-Engine Knock Tests of Methyl Tert-Butyl Ether

Description: Report presenting data that show the knock-limited performance of methyl tert-butyl ether obtained from tests made in a 17.6-cubic-inch-displacement engine under supercharged conditions. Tests for temperature sensitivity, speed sensitivity, and lead susceptibility were made on a blend of 20 percent methyl tert-butyl ether and 80 percent S-2 reference fuel.
Date: August 1944
Creator: Barnett, Henry C. & Slough, James W., Jr.
Partner: UNT Libraries Government Documents Department

Engine and inspection tests of methyl tert-butyl ether as a component of aviation fuel

Description: Report presenting an investigation of the suitability of methyl tert-butyl ether as a component of aviation fuel from considerations of knock-limited performance tests and laboratory inspection tests. Data were obtained from testing on the 17.6 engine under supercharged conditions with fuel blends containing 10 and 20 percent methyl tert-butyl ether. Results regarding small-scale-engine data, full-scale-engine data, and inspection data are provided.
Date: August 1944
Creator: Barnett, Henry C.; Meyer, Carl L. & Jones, Anthony W.
Partner: UNT Libraries Government Documents Department

Theory and Application of Hot-Wire Instruments in the Investigation of Turbulent Boundary Layers

Description: Report presenting an account of the recent developments in hot-wire instruments for use in turbulent boundary layers to determine the magnitude of the several components of the turbulent velocity fluctuations together with the correlation between them and turbulent shearing stress.
Date: March 1946
Creator: Schubauer, G. B. & Klebanoff, P. S.
Partner: UNT Libraries Government Documents Department

Experimental constriction effects in high-speed wind tunnels

Description: From Summary: "An investigation has been conducted to determine the possible extent of effects of wind-tunnel constriction at high speeds for airfoils of various thickness-to-chord ratios at or near zero lift. The results indicate that a limiting test Mach number exists which is principally a function of the ratio of model thickness to tunnel height. At high Mach numbers serious constriction effects occur; these effects are of such a nature that the standard calibration methods given speeds much lower than the actual test speeds."
Date: December 1944
Creator: Byrne, Robert W.
Partner: UNT Libraries Government Documents Department

The knock-limited performance of several miscellaneous fuels blended with a base fuel

Description: Report presenting investigations to determine the knock-limited performance of blends of 90 percent by volume AN-F-28, Amendment-2 fuel, and 10 percent by volume of the following fuels: tert-amyl alcohol, 2,6-dimethyl-1, 4-dioxane, methyl tert-butyl ether, methyl tert-butyl ketone, methyl isobutyl ketone, mesityl oxide, acetone, and diisopropyl ketone.
Date: July 1944
Creator: Bellman, Donald R.
Partner: UNT Libraries Government Documents Department

Supersonic-Tunnel Tests of Projectiles in Germany and Italy

Description: Report presenting tests performed in German and Italian supersonic tunnels to determine the aerodynamic characteristics of projectiles of various shapes. The results show that increasing the relative length of the nose causes the drag coefficient to decrease and the center of pressure to move forward.
Date: October 1945
Creator: Ferri, Antonio
Partner: UNT Libraries Government Documents Department

Estimation of Pressure Distributions at Subcritical Speeds for Turrets Located on a Wing

Description: Report presenting the use of current methods that include interference and compressibility effects to estimate pressures over and near turrets located on a wing in regions of high interference velocities. The agreement between measured and estimated pressures indicated that present methods are adequate for predicting approximate critical speeds and for estimating loads at subcritical speeds with sufficient accuracy for design purposes.
Date: July 1944
Creator: Ritchie, Virgil S. & Daniels, Everett J.
Partner: UNT Libraries Government Documents Department

Summary of Data Relating to the Effects of Wing Machine-Gun and Cannon Installations on the Aerodynamic Characteristics of Airplanes

Description: Report presenting data obtained from tests of models and airplanes relating to the effects of various wing armament installations, which have been collected and analyzed. Three types of gun installations were considered: gun ports, protruding machine guns, and cannon. The ways that each type of installation affected the lift and drag characteristics are provided.
Date: January 1945
Creator: Quinn, John H., Jr.
Partner: UNT Libraries Government Documents Department

Drag Measurements of a Protruding 0.50-Caliber Machine Gun

Description: Report presenting drag and cross-wind force measurements of a Browning 0.50-caliber M2 machine gun at a range of air speeds in the NACA wind tunnel. The gun protruded through the top of the tunnel wall into the air stream and tests were performed at a variety of angles in order to determine the power required to turn the gun against the aerodynamic forces and the horsepower absorbed in air drag by the protruding gun. Special attention is given to the jacket around the gun, which seems to provide the greatest amount of drag.
Date: July 1941
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department

Charts for Helicopter-Performance Estimation

Description: Report presenting charts relating helicopter aerodynamic design variables to performance in steady powered flight. The flight conditions covered are hovering, climb, and horizontal flight. The use of the charts is illustrated by numerical examples in order that computations can be made for particular problems.
Date: August 1945
Creator: Talkin, Herbert W.
Partner: UNT Libraries Government Documents Department

The NACA Impact Basin and Water Landing Tests of a Float Model at Various Velocities and Weights

Description: Report presenting data obtained when a float with both horizontal and vertical velocity contact on a water surface. The report is confined to a presentation of the relationship between resultant velocity and impact normal acceleration for various float weights when all other parameters are constant.
Date: August 1944
Creator: Batterson, Sidney A.
Partner: UNT Libraries Government Documents Department

Effects of Simulated Ice Formation on the Aerodynamic Characteristics of an Airfoil

Description: Report presenting an investigation of the size and distribution of ice particles on the wings of aircraft and how they affect the aerodynamic characteristics. A simulated ice formation was generated from survey information received from aircraft pilots and was tested to determine the impact on the lift characteristics.
Date: May 1938
Creator: Gulick, Beverly G.
Partner: UNT Libraries Government Documents Department

Performance of compressor-turbine jet-propulsion systems

Description: Report presenting an analysis of the performance of compressor-turbine jet-propulsion systems carried out by calculating the thrust power from a compressor-turbine jet engine with a systematic variation of pressure ratio, fuel-air ratio, compressor and turbine efficiencies, flight speed, altitude, and maximum gas temperature.
Date: June 1945
Creator: Palmer, Carl B.
Partner: UNT Libraries Government Documents Department

Consideration of Auxiliary Jet Propulsion for Assisting Take-Off

Description: Report presenting an analysis and simple method to help solve the problem of assisting the take-off of an airplane by means of auxiliary jet propulsion by determining the jet thrust and weight of jet fuel required to provide a desired reduction in take-off distance or increase in pay load or fuel load for a fixed take-off distance. The use of previous experimental work to verify the analysis is also provided.
Date: May 1940
Creator: Turner, L. Richard
Partner: UNT Libraries Government Documents Department

Flight Tests of Exhaust-Gas Jet Propulsion

Description: "Flight tests were conducted on the XP-41 airplane, equipped with a Pratt & Whitney R1830-19, 14-cylinder, air-cooled engine, to determine the increase in flight speed obtainable by the use of individual exhaust stacks directly rearwardly to obtain exhaust-gas thrust. Speed increases up to 13 miles per hour at 20,000 feet altitude were obtained using stacks having an exit area of 3.42 square inches for each cylinder. A slight increase in engine power and decrease in cylinder temperature at a given manifold pressure were obtained with the individual stacks as compared with a collector-ring installation" (p. 1).
Date: November 1940
Creator: Pinkel, Benjamin & Turner, L. Richard
Partner: UNT Libraries Government Documents Department

The Reaction Jet as a Means of Propulsion at High Speeds

Description: Report presenting a simple equation that can be used to facilitate the appraisal of the conventional jet as a means of propulsion. The equation can be used to estimate the performance of a large variety of aeropropulsive devices. The results using this equation indicate that attainable propulsive efficiencies at high speeds below sonic velocity are certain to be lower than is common at low speeds with the conventional propeller.
Date: June 1941
Creator: Williams, David T.
Partner: UNT Libraries Government Documents Department

Study of Jet-Propulsion System Comprising Blower, Burner, and Nozzle

Description: "A study was made of the performance of a jet-propulsion system composed of an engine-driven blower, a combustion chamber, and a discharge nozzle. A simplified analysis is made of this system for the purpose of showing in concise form the effect of the important design variables and operating conditions on jet thrust, thrust horsepower, and fuel consumption. Curves are presented that permit a rapid evaluation of the performance of this system for a range of operating conditions" (p. 1).
Date: May 1944
Creator: Pinkel, Benjamin & Hall, Eldon W.
Partner: UNT Libraries Government Documents Department
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