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Significance of alkylate-replacement values of aviation fuel components

Description: Report discusses the significance of alkylate-replacement values and to illustrate methods of estimating these values. Equations expressing alkylate-replacement values and the estimated effect on engine performance resulting from replacement of alkylate is discussed and test data is provided in F-3 and F-4 laboratory engines. The researchers found that "alkylate-replacement value depends not only upon the rating of the fuel component that is replacing the alkylate but also upon the ratings of the alkylate and the base fuel."
Date: December 1944
Creator: Sanders, Newell D.
Partner: UNT Libraries Government Documents Department

A Method of Estimating the Knock Rating of Hydrocarbon Fuel Blend

Description: "The usefulness of the knock ratings of pure hydrocarbon compounds would be increased if some reliable method of calculating the knock ratings of fuel blends was known. The purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends" (p. 1).
Date: 1943
Creator: Sanders, Newell D.
Partner: UNT Libraries Government Documents Department

A Method of Estimating the Knock Rating of Hydrocarbon Fuel Blends

Description: Report presenting two blending equations that have been derived from an analysis based on certain assumptions relative to the cause of fuel knock. The main purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends.
Date: August 1, 1943
Creator: Sanders, Newell D.
Partner: UNT Libraries Government Documents Department

Performance Parameters for Jet-Propulsion Engines

Description: Note presenting performance parameters for jet-propulsion engines developed from the concepts of flow similarity, inertia forces, elastic forces, viscous forces, and thermal expansions of the working fluid. The analysis relates performance to the geometry of the boundaries, Mach number, Reynolds number, and total-temperature ratio.
Date: July 1946
Creator: Sanders, Newell D.
Partner: UNT Libraries Government Documents Department

A Method of Estimating the Knock Rating of Hydrocarbon Fuel Blends

Description: "The usefulness of the knock ratings of pure hydrocarbon compounds would be increased if some reliable method of calculating the knock ratings of fuel blends was known. The purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends. Two blending equations have been derived from an analysis based on certain assumptions relative to the cause of fuel knock" (p. 1).
Date: August 1, 1943
Creator: Sanders, Newell D.
Partner: UNT Libraries Government Documents Department

Effect of varying percentages of exhaust gas on engine performance

Description: From Introduction: "These tests were run to determine the effect that mixing engine exhaust gas with engine intake air has on fuel knock limit, specific fuel consumption, and air consumption." Information about the effect on pressure, air consumption, and fuel consumption is detailed.
Date: April 1943
Creator: Sanders, Newell D. & Barnett, Henry C.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 6, Analysis of Effects of Inlet Pressure Losses

Description: The losses in the inlet air ducts, the diffusers, and the de-icing equipment associated with turbojet engine installations cause a reduction in the total pressure at the inlet of the engine and result in reduced thrust and increased specific fuel consumption. An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of a 3000-pound-thrust axial flow turbojet engine with a two-stage turbine is presented. The analysis is based on engine performance characteristics that were determined from experiments in the NACA Cleveland altitude wind tunnel. The experimental investigation did not include tests in which inlet losses were systematically varied, but the effects of these losses can be accurately estimated from the experimentally determined performance characteristics of the engine.
Date: 1948
Creator: Sanders, Newell D. & Palasics, John
Partner: UNT Libraries Government Documents Department

Analysis of Effects of Inlet Pressure Losses on Performance of Axial-Flow Type Turbojet Engine

Description: From Introduction: "An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of an axial-flow-compressor type turbojet engine with a two-stage turbine is presented herein. The analysis is based on engine performance characteristics that were determined from experiments in the NACA Cleveland altitude wind tunnel (references 1 and 2). The experimental investigation did not include tests in which inlet losses were systematically varied, but the effects of these losses can be accurately estimated from the experimentally determined performance characteristics of the engine."
Date: November 24, 1948
Creator: Sanders, Newell D. & Palasics, John
Partner: UNT Libraries Government Documents Department

Application of Pulse Techniques to Strain Gages

Description: Memorandum presenting pulse techniques applied to strain gages for increasing the output level and extending the usable range. Bonded and unbonded strain gages which normally operate with exciting potentials between 3.5 and 14 volts operated satisfactorily with 200-volt pulses of 1-microsecond duration and a repetition rate of 350 per second. Results regarding maximum allowable voltages, effective pulse duration, sensitivity, minimum readable signal, effects of cable capacitance and inductance, sensitivity to external noise, and linearity are provided.
Date: May 4, 1954
Creator: Sanders, Newell D. & Brodie, George H.
Partner: UNT Libraries Government Documents Department

Experimental Studies of the Knock-Limited Blending Characteristics of Aviation Fuels 2: Investigation of Leaded Paraffinic Fuels in an Air-Cooled Cylinder

Description: Note presenting the relation between knock limit and blend composition of selected aviation fuel components individually blended with virgin base and with alkylate as determined in a full-scale air-cooled aircraft-engine cylinder. Results regarding mixture-response curves, relation of knock limit to blend composition, and correlation of knock ratings are provided.
Date: July 1947
Creator: Wear, Jerrold D. & Sanders, Newell D.
Partner: UNT Libraries Government Documents Department

Relative effects of cylinder-head and inlet-mixture temperatures upon knock limits of fuels

Description: Report discusses an investigation into the relation between the effects of cylinder-head temperature and inlet-mixture temperature on the knock limits of fuels. The tests were run at a constant fuel-air ratio and the decrease in cylinder-head temperature required to offset the effect of increasing the inlet-mixture temperature on knock-limited power was determined. The apparatus and testing procedure are described and the effect of changes in cylinder-head temperature on the knock limit of any fuel are plotted.
Date: October 1944
Creator: Sanders, Newell D.; Wear, Jerrold D. & Hensley, Reece V.
Partner: UNT Libraries Government Documents Department

Effect of inlet-air temperature and cylinder displacement on charge temperature of internal combustion engines

Description: Report discussing the effect of inlet-air temperature and cylinder displacement on the charge temperature of an internal-combustion engine at the end of the induction stroke. The experiment to test various types of cylinders and their results on the air temperature and pressure is described.
Date: January 1944
Creator: Sanders, Newell D. & Bolz, Ray E.
Partner: UNT Libraries Government Documents Department

Cooling of ram jets and tail-pipe burners: analytical method for determining temperatures of combustion chamber having annular cooling passage

Description: Report presenting an analytical method for calculating the maximum wall temperature of a tail-pipe burner or a ramjet combustion chamber cooled by air or gas flowing through a surrounding annular passage.
Date: March 21, 1950
Creator: Koffel, William K.; Stamper, Eugene & Sanders, Newell D.
Partner: UNT Libraries Government Documents Department

Experimental Studies of the Knock-Limited Blending Characteristics of Aviation Fuels 1: Preliminary Tests in an Air-Cooled Cylinder

Description: Report presenting an investigation of the relation between the knock limit and the blend composition of aviation fuels when tested under supercharged conditions in an air-cooled aircraft-engine cylinder. Results regarding the blending characteristics of two gasolines, paraffinic fuels, olefinic fuel, naphthenic fuel, aromatic fuels, when xylidines are present in the fuel components, and fuel components containing unequal concentrations of tetraethyl lead are provided.
Date: October 1944
Creator: Sanders, Newell D.; Hensley, Reece V. & Breitwieser, Roland
Partner: UNT Libraries Government Documents Department