Comparison of Alcogas Aviation Fuel With Export Aviation Gasoline (open access)

Comparison of Alcogas Aviation Fuel With Export Aviation Gasoline

Mixtures of gasoline and alcohol when used in internal combustion engines designed for gasoline have been found to possess the advantage of alcohol in withstanding high compression without "knock" while retaining advantages of gasoline with regard to starting characteristics. Test of such fuels for maximum power-producing ability and fuel economy at various rates of consumption are thus of practical importance, with especial reference to high-compression engine development. This report discusses the results of tests which compares the performance of alcogas with x gasoline (export grade) as a standard.
Date: November 25, 1919
Creator: Gage, V. R.; Sparrow, S. W. & Harper, D. R.
System: The UNT Digital Library
The relative performance obtained with several methods of control of an overcompressed engine using gasoline (open access)

The relative performance obtained with several methods of control of an overcompressed engine using gasoline

"This report presents some results obtained during an investigation to determine the relative characteristics for several methods of control of an overcompressed engine using gasoline and operating under sea-level conditions. For this work, a special single cylinder test engine, 5-inch bore by 7-inch stroke, and designed for ready adjustment of compression ratio, valve timing and valve lift while running, was used. This engine has been fully described in NACA-TR-250. Tests were made at an engine speed of 1,400 R. P. M. for compression ratios ranging from 4.0 to 7.6" (p. 329).
Date: February 25, 1927
Creator: Gardiner, Arthur W. & Whedon, William E.
System: The UNT Digital Library
The N.A.C.A. photographic apparatus for studying fuel sprays from oil engine injection valves and test results from several researches (open access)

The N.A.C.A. photographic apparatus for studying fuel sprays from oil engine injection valves and test results from several researches

"Apparatus for recording photographically the start, growth, and cut-off of oil sprays from injection valves has been developed at the Langley Memorial Aeronautical Laboratory. The apparatus consists of a high-tension transformer by means of which a bank of condensers is charged to a high voltage. The controlled discharge of these condensers in sequence, at a rate of several thousand per second, produces electric sparks of sufficient intensity to illuminate the moving spray for photographing. The sprays are injected from various types of valves into a chamber containing gases at pressures up to 600 pounds per square inch" (p. 361).
Date: May 25, 1927
Creator: Beardsley, Edward G.
System: The UNT Digital Library
The Gaseous Explosive Reaction: A Study of the Kinetics of Composite Fuels (open access)

The Gaseous Explosive Reaction: A Study of the Kinetics of Composite Fuels

"This report deals with the results of a series of studies of the kinetics of gaseous explosive reactions where the fuel under observation, instead of being a simple gas, is a known mixture of simple gases. In the practical application of the gaseous explosive reaction as a source of power in the gas engine, the fuels employed are composite, with characteristics that are apt to be due to the characteristics of their components and hence may be somewhat complex" (p. 503).
Date: April 25, 1928
Creator: Stevens, F. W.
System: The UNT Digital Library
Working Charts for the Selection of Aluminum Alloy Propellers of a Standard Form to Operate With Various Aircraft Engines and Bodies (open access)

Working Charts for the Selection of Aluminum Alloy Propellers of a Standard Form to Operate With Various Aircraft Engines and Bodies

"Working charts are given for the convenient selection of aluminum alloy propellers of a standard form, to operate in connection with six different engine-fuselage combinations. The charts have been prepared from full-scale test data obtained in the 20-foot propeller research tunnel of the National Advisory Committee for Aeronautics. An example is also given showing the use of the charts" (p. 3).
Date: March 25, 1929
Creator: Weick, Fred E.
System: The UNT Digital Library
Comparative flight performance with an NACA Roots supercharger and a turbocentrifugal supercharger (open access)

Comparative flight performance with an NACA Roots supercharger and a turbocentrifugal supercharger

This report presents the comparative flight results of a roots supercharger and a turbocentrifugal supercharger. The tests were conducted using a modified DH-4M2 airplane. The rate of climb and the high speed in level flight of the airplane were obtained for each supercharger from sea level to the ceiling. The unsupercharged performance with each supercharger mounted in place was also determined. The results of these tests show that the ceiling and rate of climb obtained were nearly the same for each supercharger, but that the high speed obtained with the turbocentrifugal was better than that obtained with the roots. The high-speed performance at 21,000 feet was 122 and 142 miles per hour for the roots and turbocentrifugal, respectively.
Date: February 25, 1930
Creator: Schey, Oscar W. & Young, Alfred W.
System: The UNT Digital Library
The effect on airplane performance of the factors that must be considered in applying low-drag cowling to radial engines (open access)

The effect on airplane performance of the factors that must be considered in applying low-drag cowling to radial engines

From Summary: "This report presents the results of flight tests with three different airplanes using several types of low-drag cowling for radial air-cooled engines. The greater part of the tests were made with a Curtiss XF7Cc-1 (Sea Hawk) with a 410 horsepower. Wasp engine, using three fuselage nose shapes and six types of outer cowling. The six cowlings were: a narrow ring, a wide ring, a wide cowling similar in the original NACA cowling, a thick ring incorporating an exhaust collector, a single-surface cowling shaped like the outer surface of the exhaust-collector cowling, and polygon-ring cowling, of which the angle of the straight sections with the thrust line could be varied over a wide range."
Date: November 25, 1931
Creator: McAvoy, William H.; Schey, Oscar W. & Young, Alfred W.
System: The UNT Digital Library
Preliminary Investigation of Modifications to Conventional Airplanes to Give Nonstalling and Short-Landing Characteristics (open access)

Preliminary Investigation of Modifications to Conventional Airplanes to Give Nonstalling and Short-Landing Characteristics

"This report describes flight and landing tests made on a group of conventional airplanes. The upward deflection of the elevators was limited to the point where the airplanes could not be made to spin without the aid of power. With the elevator travel thus limited, the airplane in every case had good lateral stability and good aileron effectiveness up to the highest angles of attack which could be obtained in a glide, although this was not true in any case without the limited control" (p. 343).
Date: January 25, 1932
Creator: Weick, Fred E.
System: The UNT Digital Library
Some Effects of Argon and Helium Upon Explosions of Carbon Monoxide and Oxygen (open access)

Some Effects of Argon and Helium Upon Explosions of Carbon Monoxide and Oxygen

Report presents the results of an investigation conducted to study the effects of the inert gases, argon and helium, upon flame speed and expansion ratio in exploding mixtures of carbon monoxide, oxygen and water. For the particular gas mixtures investigated the results show that: (1) With the possible exception of helium in small amounts the addition of inert gas always produces decreased flame speed and expansion ratio; (2) like volumes of argon and helium have very different effects upon flame speed but practically the same effect upon expansion ratio; and (3) the difference in the effect of these two gases upon speed is independent of the ratio of carbon monoxide to oxygen. A discussion of some possible modes by which inert gases may produce the observed effects is included.
Date: September 25, 1935
Creator: Fiock, Ernst F. & Roeder, Carl H.
System: The UNT Digital Library
Wind-Tunnel Investigation of Ordinary and Split Flaps on Airfoils of Different Profile (open access)

Wind-Tunnel Investigation of Ordinary and Split Flaps on Airfoils of Different Profile

Report presents the results of wind tunnel tests of the Clark Y, the NACA 23012 and the NACA 23021 airfoils equipped with full-span ordinary flaps and with full-span simple split flaps. The principal object of the tests was to determine the characteristics of the airfoils with ordinary flaps and in addition, to determine the relative merits of the various airfoils when equipped with either ordinary flaps or with simple split flaps. The Clark Y airfoil was tested with 3 widths of ordinary flap, 10, 20, and 30 percent of the airfoil chord.
Date: October 25, 1935
Creator: Wenzinger, Carl J.
System: The UNT Digital Library
Calculated and measured pressure distributions over the midspan section of the NACA 4412 airfoil (open access)

Calculated and measured pressure distributions over the midspan section of the NACA 4412 airfoil

Pressures were simultaneously measured in the variable-density tunnel at 54 orifices distributed over the midspan section of 5 by 30 inch rectangular model of the NACA 4412 airfoil at 17 angles of attack ranging from -20 degrees to 30 degrees at a Reynolds number of approximately 3,000,000. Accurate data were thus obtained for studying the deviations of the results of potential-flow theory from measured results. The results of the analysis and a discussion of the experimental technique are presented.
Date: March 25, 1936
Creator: Pinkerton, Robert M.
System: The UNT Digital Library
Heat Transfer to Fuel Sprays Injected Into Heated Gases (open access)

Heat Transfer to Fuel Sprays Injected Into Heated Gases

This report presents the results of a study made of the influence of several variables on the pressure decrease accompanying injection of a relatively cool liquid into a heated compressed gas. Indirectly, this pressure decrease and the time rate of change of it are indicative of the total heat transferred as well as the rate of heat transfer between the gas and the injected liquid. Air, nitrogen, and carbon dioxide were used as ambient gases; diesel fuel and benzene were the injected liquids. The gas densities and gas-fuel ratios covered approximately the range used in compression-ignition engines. The gas temperatures ranged from 150 degrees c. to 350 degrees c.
Date: August 25, 1936
Creator: Selden, Robert F. & Spencer, Robert C.
System: The UNT Digital Library
Fuel spray and flame formation in a compression-ignition engine employing air flow (open access)

Fuel spray and flame formation in a compression-ignition engine employing air flow

"The effects of air flow on fuel spray and flame formation in a high-speed compression-ignition engine have been investigated by means of the NACA combustion apparatus. The process was studied by examining high-speed motion pictures taken at the rate of 2,200 frames a second. The combustion chamber was of the flat-disk type used in previous experiments with this apparatus. The air flow was produced by a rectangular displacer mounted on top of the engine piston. Three fuel-injection nozzles were tested: a 0.020-inch single-orifice nozzle, a 6-orifice nozzle, and a slit nozzle" (p. 281).
Date: November 25, 1936
Creator: Rothrock, A. M. & Waldron, C. D.
System: The UNT Digital Library
Static Thrust and Power Characteristics of Six Full-Scale Propellers (open access)

Static Thrust and Power Characteristics of Six Full-Scale Propellers

"Static thrust and power measurements were made of six full-scale propellers. The propellers were mounted in front of a liquid-cooled-engine nacelle and were tested at 15 different blade angles in the range from -7 1/2 degrees to 35 degrees at 0.75r. The test rig was located outdoors and the tests were made under conditions of approximately zero wind velocity" (p. 85).
Date: January 25, 1939
Creator: Hartman, Edwin P. & Biermann, David
System: The UNT Digital Library
Effect of Normal Pressure on the Critical Compressive Stress of Curved Sheet (open access)

Effect of Normal Pressure on the Critical Compressive Stress of Curved Sheet

Results are presented of tests of two specimens tested to study the effect of normal pressure on the critical compressive stress for thin curved sheets. These specimens are designated by their respective rib spacings of 10 inches and 30 inches. The relationship between compressive stress and normal pressure at which buckles disappeared is independent of whether the buckles were made to disappear by increase of normal pressure or decrease of compressive stress. (author).
Date: August 25, 1942
Creator: Rafel, Norman
System: The UNT Digital Library
Intercooler cooling-air weight flow and pressure drop for minimum drag loss (open access)

Intercooler cooling-air weight flow and pressure drop for minimum drag loss

An analysis has been made of the drag losses in airplane flight of cross-flow plate and tubular intercoolers to determine the cooling-air weight flow and pressure drop that give a minimum drag loss for any given cooling effectiveness and, thus, a maximum power-plant net gain due to charge-air cooling. The drag losses considered in this analysis are those due to (1) the extra drag imposed on the airplane by the weight of the intercooler, its duct, and its supports and (2) the drag sustained by the cooling air in flowing through the intercooler and its duct. The investigation covers a range of conditions of altitude, airspeed, lift-drag ratio, supercharger-pressure ratio, and supercharger adiabatic efficiency. The optimum values of cooling air pressure drop and weight flow ratio are tabulated. Curves are presented to illustrate the results of the analysis.
Date: February 25, 1944
Creator: Reuter, J. George & Valerino, Michael F.
System: The UNT Digital Library
Flight measurements of horizontal tail loads on a typical propeller-driven pursuit airplane during stalled pull-outs at high speed (open access)

Flight measurements of horizontal tail loads on a typical propeller-driven pursuit airplane during stalled pull-outs at high speed

Report presenting flight measurements of the pressures on the horizontal tail surfaces of a typical propeller-driven pursuit airplane during stalled pull-outs at high Mach number. Unit loads measured on the stabilizer at safe maneuvering limits were not only considerably in excess of the design unit loads, but also occurred in a direction opposite to the design loads. Revision of the tail-load design requirements and manner of specifying safe maneuverability limits to pilots appears necessary.
Date: April 25, 1944
Creator: Clousing, Lawrence A. & Turner, William N.
System: The UNT Digital Library
Altitude-wind-tunnel investigations of thrust augmentation of a turbojet engine 1: Performance with tail-pipe burning (open access)

Altitude-wind-tunnel investigations of thrust augmentation of a turbojet engine 1: Performance with tail-pipe burning

From Introduction: "Performance results of the tail-pipe burning investigation on the TG-180 turbojet engine and a comparison of experimental results with theoretical calculations are presented."
Date: September 25, 1946
Creator: Fleming, W. A. & Dietz, R. O.
System: The UNT Digital Library
Flight measurements of the lateral control characteristics of narrow-chord ailerons on the trailing edge of a full-span slotted flap (open access)

Flight measurements of the lateral control characteristics of narrow-chord ailerons on the trailing edge of a full-span slotted flap

From Summary: "Results are presented of light tests made to determine the effect of flap deflection on the lateral control characteristics of a modified Brewster F2A-2 airplane equipped with partial-span narrow-chord ailerons on the trailing edge of a full-span NACA slotted flap. The investigation included determination of the rolling and yawing characteristics of the airplane in abrupt aileron rolls with the slotted flap at various settings ranging from 0 degree to about 40 degrees. The results showed that the effectiveness of the ailerons was greatly reduced at flap deflections greater than about 20 degrees. For flap deflections up to about 20 degrees, the aileron effectiveness was about the same as with flaps retracted, but the adverse yawing velocity developed in the abrupt aileron rolls was somewhat increased."
Date: October 25, 1946
Creator: Sawyer, Richard H.
System: The UNT Digital Library
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines: 4 - Analysis of Compressor Performance (open access)

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines: 4 - Analysis of Compressor Performance

"Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and operational characteristics of the 19B-2, 19B-8, and 19XS-1 turbojet engines. One objective was to determine the effect of altitude, flight Mach number, and tail-pipe-nozzle area on the performance characteristics of the six-stage and ten-stage axial-flow compressors of the 19B-8 and 19XB-1 engines, respectively, The data were obtained over a range of simulated altitudes and flight Mach numbers" (p. 1).
Date: April 25, 1947
Creator: Dietz, Robert O. & Kuenzig, John K.
System: The UNT Digital Library
Effects of Compressibility on the Characteristics of Five Airfoils (open access)

Effects of Compressibility on the Characteristics of Five Airfoils

Report presenting the results of pressure-distribution tests to determine the effects of compressibility on the characteristics of the NACA 66,2-215, 66,2-015, 65(216)-418, 16-212, and 23015 airfoil sections. Schileren photographs of the air flow and data on the wake characteristics was also obtained.
Date: April 25, 1947
Creator: Daley, Bernard N.
System: The UNT Digital Library
Flight Observations of Aileron Flutter at High Mach Numbers as Affected by Several Modifications (open access)

Flight Observations of Aileron Flutter at High Mach Numbers as Affected by Several Modifications

Report presenting an investigation of aileron flutter associated with high-speed flight. When the aileron control system was modified by installing a hydraulic irreversible unit, it was possible to delay aileron flutter and reduce its amplitude. Results regarding the aileron flutter with and without the modifications, analysis of the time histories for the control systems, and relation between aileron upfloat and flutter are provided.
Date: April 25, 1947
Creator: Spreiter, John R.; Galster, George M. & Cooper, George E.
System: The UNT Digital Library
Flight-Test Evaluation of the Longitudinal Stability and Control Characteristics of 0.5-Scale Models of the Fairchild Lark Pilotless-Aircraft Configuration: Standard Configuration with Wing Flaps Deflected 60 Degrees and Model having Tail in Line with Wings, TED No. NACA 2387 (open access)

Flight-Test Evaluation of the Longitudinal Stability and Control Characteristics of 0.5-Scale Models of the Fairchild Lark Pilotless-Aircraft Configuration: Standard Configuration with Wing Flaps Deflected 60 Degrees and Model having Tail in Line with Wings, TED No. NACA 2387

Flight tests were conducted at the Flight Test Station of the Pilotless Aircraft Research Division at Wallop Island, Va., to determine the longitudinal control and stability characteristics of 0.5-scale models of the Fairchild Lark pilotless aircraft with the tail in line with the wings a d with the horizontal wing flaps deflected 60 deg. The data were obtained by the use of a telemeter and by radar tracking.
Date: June 25, 1947
Creator: Stone, David G.
System: The UNT Digital Library
Performance of a 20-inch steady-flow ram jet at high altitudes and ram-pressure ratios (open access)

Performance of a 20-inch steady-flow ram jet at high altitudes and ram-pressure ratios

Report presenting the results of an investigation conducted in the altitude wind tunnel to determine the performance of a 20-inch ramjet. The investigation was conducted at a range of altitudes and ram-pressure ratios using preheated 62-octane fuel. A net thrust of 8135 pounds educed to standard sea-level conditions, a net-thrust coefficient of 0.74, and an overall efficiency of 12.6 percent were attained at Mach number 1.845 at which the engine with a 5-foot combustion chamber was operated.
Date: June 25, 1947
Creator: Perchonok, Eugene; Sterbentz, William H. & Wilcox, Fred A.
System: The UNT Digital Library