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Summary of the Availability and Performance Problems of High Octane Number Fuels

Description: Memorandum presenting a study to determine the possible blending agents or additives that may be used to supplement current high performance number, rich rating components in future aviation fuels. The study indicated that such high rich rating blending agents as toluene and xylene cannot be made available in sufficient quantities to maintain the rich rating performance of the fuels when reducing the lead content from 4.6 to 3.0 ml per gallon.
Date: April 15, 1949
Creator: NACA Committee on Aircraft Fuels
Partner: UNT Libraries Government Documents Department

Effects of Small Angles of Sweep and Moderate Amounts of Dihedral on Stalling and Lateral Characteristics of a Wing-Fuselage Combination Equipped With Partial- and Full-Span Double Slotted Flaps

Description: "Tests of a wing-fuselage combinations incorporating NACA 65-series airfoil sections were conducted in the NACA 19-foot pressure tunnel. The investigation included the tests with flaps neutral and with partial- and full-span double slotted flaps deflected to determine the effects of (1) variations of wing sweep between -4 degrees and 8 degrees on stalling and lateral stability and control characteristics and (2) variations of dihedral between 0 degree and 6.75 degrees on lateral stability characteristics" (p. 467).
Date: April 15, 1944
Creator: Teplitz, Jerome
Partner: UNT Libraries Government Documents Department

A Summary Report on the Effects of Mach Number on the Span Load Distribution on Wings of Several Models

Description: Memorandum presenting an investigation of the change in spanwise load distribution at high Mach numbers, which is of considerable interest because lateral movement of the center of lift affects the trim, stability, and structural factors of safety of an airplane. The data is not sufficient to permit isolation of the effects of changes in wing configuration, but in a majority of cases, the tests reveal a tendency for the center of lift to shift outboard with increasing Mach number.
Date: July 15, 1947
Creator: Jessen, Henry, Jr.
Partner: UNT Libraries Government Documents Department

Comparison of Effectiveness of Coordinated Turns and Level Sideslips for Correcting Lateral Displacement During Landing Approaches

Description: Memorandum presenting a calculation of the amount of possible correction for coordinated turns with limited bank angle and level sideslips for a large transport airplane, the C-54D. The results indicate that for all instances from the end of the runway, coordinated turns are the more effective maneuver.
Date: December 15, 1949
Creator: Faber, Stanley
Partner: UNT Libraries Government Documents Department

Combustion-efficiency investigation of special fuels in single tubular-type combustor at simulated altitude conditions

Description: Report presenting a combustion-efficiency investigation of 10 special straight-run distillate fuels in an individual tubular-type combustor unit of a 14-unit assembly at two simulated engine operating conditions. These distillates were obtained from various crude oils and consisted of hydrocarbon mixtures with distillations temperature varying from 93 to 690 degrees Fahrenheit. Comparison of temperature measurements obtained from two locations in the exhaust duct showed that under certain operating conditions the flame extended beyond the turbine position.
Date: August 15, 1947
Creator: Dittrich, Ralph T.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, February 15, 1943 : week of February 5 to February 12

Description: Front: Text describes action on various war fronts: Command, Solomons, North Africa, New Guinea, Russia. Large world map is keyed to text and illustrates time zones around the world. Inset maps of Guadalcanal; Russian front. Photographs: Heads down [under the barbed wire]; Jap navel gun; Near the end [fighting in Papua]; North Africa; Poles in Iraq; Vital supply: water for the Eighth Army; German mortar. Back: Poster illustrates uniforms and insignia of the German Army.
Date: February 15, 1943
Creator: [United States.] Army Orientation Course.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, March 15, 1943 : week of March 5 to March 12, 183rd week of the war, 65th week of U.S. participation

Description: Front: Text describes action on various war fronts: Russia, Air offensive, Unrest (France, Belgium, Norway), Southwest Pacific, Tunisia. Large world map is keyed to text and illustrates time zones around the world. Inset maps show Russia, Tunisia. Includes photographs: Convoy to Russia; American tank in Russia; Joint Assignment; Airborne engineers; Shower bath - desert style. Back: Learn to recognize these vehicles (half-track vehicles). Labelled illustrations of American, Canadian and German vehicles with a quick guide to features for comparison.
Date: March 15, 1943
Creator: [United States.] Army Orientation Course.
Partner: UNT Libraries Government Documents Department

Application of Theodorsen's theory to propeller design

Description: A theoretical analysis is presented for obtaining, by use of Theodorsen's propeller theory, the load distribution along a propeller radius to give the optimum propeller efficiency for any design condition. The efficiencies realized by designing for the optimum load distribution are given in graphs, and the optimum efficiency for any design condition may be read directly from the graph without any laborious calculations. Examples are included to illustrate the method of obtaining the optimum load distributions for both single-rotating and dual-rotating propellers.
Date: March 15, 1948
Creator: Crigler, John L.
Partner: UNT Libraries Government Documents Department

Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 4: some effects of internal duct shape upon an inlet enclosing 37.2 percent of the forebody circumference

Description: Report presenting tests to determine the recovery of total pressure attainable at a range of Mach numbers, which were performed with models with twin-scoop inlets situated on the sides of a long forebody. Results regarding ducts without slots and ducts with slots are provided.
Date: March 15, 1949
Creator: Davis, Wallace F.; Edwards, Sherman S. & Brajnikoff, George B.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Low-Speed Characteristics of a 1/8-Scale Model of the Republic XP-91 Airplane with a Vee and a Conventional Tail

Description: "Low-speed wind-tunnel tests of a l/8 scale model of the Republic XP-91 airplane were made to determine its low-speed characteristics and the relative merits of a vee and a conventional tail on the model. The results of the tests showed that for the same amount of longitudinal and directional stability the conventional tail gave less roll due to sideslip than did the vee tail. The directional stability of the model was considered inadequate for both the vee and conventional tails; however, increasing the area and aspect ratio of the conventional vertical tail provided adequate directional stability" (p. 1).
Date: December 15, 1947
Creator: Weiberg, James A. & Anderson, Warren E.
Partner: UNT Libraries Government Documents Department

Flow studies in the asymmetric adjustable nozzle of the Ames 6-by 6-foot supersonic wind tunnel

Description: Report presenting surveys of the flow of the asymmetric adjustable nozzle of the 6- by 6-foot supersonic wind tunnel, which were made to determine the uniformity of the air stream. Test techniques for minimizing the effects of stream irregularities and the results of force and pressure-distribution tests of a swept-wing model are presented to illustrate the effectiveness of these techniques.
Date: September 15, 1949
Creator: Frick, Charles W. & Olson, Robert N.
Partner: UNT Libraries Government Documents Department

Analysis of variation of piston temperature with piston dimensions and undercrown cooling

Description: From Summary: "A theoretical analysis is presented that permits estimation of the changes in piston-temperature distribution induced by variations in the crown thickness, the ring-groove-pad thickness, and the undercrown surface heat-transfer coefficient. The analysis consists of the calculation of operating temperatures at various points in the piston body on the basis of the experimentally determined surface heat-transfer coefficients and boundary-region temperatures, as well as arbitrarily selected surface coefficients."
Date: January 15, 1948
Creator: Sanders, J. C. & Schramm, W. B.
Partner: UNT Libraries Government Documents Department

Evaluation of piston-type gas-generator engine for subsonic transport operation

Description: Report presenting an evaluation of a piston-type gas-generator engine by comparing the performance of a transport airplane powered with than engine with the same airplane powered by different engines. The engines compared were a turbojet engine, a turbine-propeller engine, a compound engine, and a turbosupercharged reciprocating engine utilizing a variable-area exhaust jet nozzle. Results regarding optimum altitude and transport performance are provided.
Date: July 15, 1949
Creator: Lietzke, A. F. & Henneberry, Hugh M.
Partner: UNT Libraries Government Documents Department

Reynolds number effect on axial-flow compressor performance

Description: Investigation conducted in the altitude wind tunnel to study the effect of Reynolds number on the performance of an axial-flow compressor. The compressor was operated as a part of a turbojet engine over a range of pressure altitudes and compressor-inlet Reynolds numbers. Results regarding compressor efficiency, air flow, and a comparison with axial-flow compressors of different design are provided.
Date: September 15, 1949
Creator: Wallner, Lewis E. & Fleming, William A.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of effects of combustion in ram jet on performance of supersonic diffusers 1: shock diffuser with triple-shock projecting cone

Description: Report presenting an investigation in the 20-inch supersonic tunnel at Mach number 1.92 with a 3.6-inch-diameter ram jet to determine the effects of combustion on the performance of a shock diffuser with a triple-shock projecting cone. Results are presented for a range of outlet areas and fuel flows with both single- and split-fuel-injection systems. Results regarding diffuser performance with combustion, combustion with constant outlet-inlet area ratio, combustion with constant fuel flow, diffuser performance with combustion, and Mach number distribution at the diffuser outlet are provided.
Date: September 15, 1948
Creator: Connors, J. F. & Schroeder, A. H.
Partner: UNT Libraries Government Documents Department

Experimental performance of chlorine trifluoride-hydrazine propellant combination in 100-pound-thrust rocket engine

Description: Report presenting an investigation of the experimental performance of chlorine triflouride and hydrazine measured over a range of propellant mixtures in a 100-pound-thrust rocket engine. Experimental values of specific impulse, volume specific impulse, heat rejection per propellant weight, nozzle thrust coefficient, and characteristic velocity were obtained as functions of percent fuel by weight in the propellant mixture.
Date: August 15, 1949
Creator: Ordin, Paul M. & Miller, Riley O.
Partner: UNT Libraries Government Documents Department

Stability and control characteristics of a free-flying model with an unswept wing of aspect ratio 3 (XS-3)

Description: The results of power-off force tests and flight tests of a model with a thin unswept low-aspect-ratio wing are presented. The tests were made with the flaps retracted and deflected. The effects on the lateral flight characteristics of decreasing directional stability were noted.
Date: November 15, 1948
Creator: Bennett, Charles V. & Hassell, James L., Jr.
Partner: UNT Libraries Government Documents Department