Technical Report Archive & Image Library (TRAIL) - 37 Matching Results

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Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model

Description: From Introduction: "The heat-transfer data calculated from measured temperatures are compared with values calculated by the theory of Van Driest for a flat plate with laminar and turbulent boundary layers. In addition, the heat-transfer data from the flight tests are compared with data obtained from the Langley Structures Research Division of ground tests of an identical wing at a Mach number approximately equal to 1.99 in the pre-flight jet of the Langley Pilotless Aircraft Research Station a… more
Date: August 6, 1957
Creator: Strass, H. Kurt & Stephens, Emily W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airplane Measurements of Atmospheric Turbulence for Altitudes Between 20,000 and 55,000 Feet Over the Western Part of the United States

Description: Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.
Date: August 23, 1957
Creator: Coleman, Thomas L. & Coe, Emilie C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Description: From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
Date: August 19, 1957
Creator: Braithwaite, Willis M.; Fenn, David B. & Algranti, Joseph S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of two-stage-turbine efficiency characteristics in terms of work and speed requirements

Description: From Introduction: "In this report two-stage-turbine efficiency characteristics are analyzed as a function of work and speed requirements in terms of the effect of changing the required mean-section velocity diagram. The fundamental assumptions and limits used in reference 2 and 3 are also used herein."
Date: August 30, 1957
Creator: Stewart, Warner L. & Wintucky, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Brief Analog Investigation of Inertia Coupling in Rolling Maneuvers of an Airplane Configuration Using a Variable-Incidence Wing as the Longitudinal Control

Description: "An analog computer study was made in order to investigate the inertia coupling in rolling maneuvers of an airplane configuration utilizing a variable-incidence wing for longitudinal control. A five-degree-of-freedom system of equations was used, and only one set of flight conditions was included in this study. The results, when compared to those for a conventional tail-control airplane, indicated significant advantages for the variable-incidence-wing type of control in reducing undesired dynam… more
Date: August 6, 1957
Creator: Gillis, Clarence L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Design and Cascade Tests of Free-Streamline and Full-Contour 160 Degree Turning Supersonic-Turbine-Blade Sections

Description: Memorandum presenting the flow characteristics of two supersonic-impulse-turbine-blade sections designed for a turning angle of 160 degrees. Results regarding the full-contour blade, free streamline blades, and a comparison of the performance are provided.
Date: August 16, 1957
Creator: Westphal, Willard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The design and cascade tests of free-streamline and full-contour 160 degrees turning supersonic-turbine-blade sections

Description: Report presenting a study of the flow characteristics of two supersonic-impulse-turbine-blade sections designed for a turning angle of 160 degrees. The primary difference between the two sections was the cutting away of a large portion of the convex surface and the presence of a free streamline as the boundary of flow in the passage. Results regarding the full-contour blade, free-streamline blade, and a comparison of the two are provided.
Date: August 16, 1957
Creator: Westphal, Willard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design and performance of flight-type liquid-hydrogen heat exchanger

Description: Report presenting an investigation of a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. The heat exchanger was evaluated in an altitude test chamber in conjunction with the complete aircraft fuel system. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date: August 19, 1957
Creator: Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design and performance of flight-type liquid-hydrogen heat exchanger

Description: Report presenting a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. A ram-air heat exchanger was used to vaporize liquid hydrogen. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date: August 19, 1957
Creator: Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System

Description: Memorandum presenting the system analysis, design, and performance of a control system for an experimental flight-type hydrogen fuel system. The fuel system was designed to investigate some of the problems associated with the utilization of hydrogen as an aircraft fuel. Speed control of the engine was obtained by coupling the hydrogen regulator to the JP-4 fuel control.
Date: August 19, 1957
Creator: Otto, Edward W.; Hiller, Kirby W. & Ross, Phil S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System

Description: Report presenting the system analysis, design, and performance of a control system for an experimental flight-type hydrogen fuel system. The system was designed to explore some problems associated using hydrogen as an aircraft fuel. Results regarding the steady-state response, transient response, and performance in engine-speed loop for the system are provided.
Date: August 19, 1957
Creator: Otto, Edward W.; Hiller, Kirby W. & Ross, Phil S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drop burning rates of hydrocarbon and nonhydrocarbon fuels

Description: An investigation of the burning rates of single drops of 15 hydrocarbon and nonhydrocarbon fuels in quiescent air at room temperature and pressure. The drop burning rates were found to be proportional to drop diameter. The experimentally determined drop burning rates were in orderly agreement with those predicted by theoretical analysis, but the absolute values differed significantly.
Date: August 6, 1957
Creator: Smith, Arthur L. & Graves, Charles C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Nose Shape on Subsonic Aerodynamic Characteristics of a Body of Revolution Having a Fineness Ratio of 10.94

Description: Memorandum presenting a determination of the effect of nose shape on the normal-force, pitching-moment, and axial-force coefficients of a body of revolution with a fineness ratio of 10.94 as determined at subsonic speeds. Six nose shapes were investigated, which included flat-faced noses with various corner radii, a hemispherical nose, and two ogival noses.
Date: August 12, 1957
Creator: Polhamus, Edward C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Control Profile on the Oscillating Hinge-Moment and Flutter Characteristics of a Flap-Type Control at Transonic Speeds

Description: Report discussing testing to determine the effects of control profile on the dynamic hinge-moment and flutter characteristics of a trailing-edge flap-type control. A conventional control and two control profile modifications were examined. Information about spring moments is also provided.
Date: August 23, 1957
Creator: Moseley, William C., Jr. & Price, George W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Internal-Area Distribution, Spike Translation, and Throat Boundary-Layer Control on Performance of a Double-Cone Axisymmetric Inlet at Mach Numbers From 3.0 to 2.0

Description: Report presenting an investigation to determine the effects of initial subsonic diffusion rate, variable geometry, and throat boundary-layer control on the performance of an axisymmetric double-cone inlet. Major gains in performance at higher Mach numbers were obtained with boundary-layer control in the form of a ram scoop at the throat. Results regarding the effect of internal-area distribution, effect of spike translation, and effect of throat boundary-layer control are provided.
Date: August 30, 1957
Creator: Connors, James F.; Lovell, J. Calvin & Wise, George A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Jet Exhausts on Flight-Determined Longitudinal and Lateral Dynamic Stability Characteristics of the Douglas D-558-II Research Airplane

Description: Memorandum presenting a flight investigation using pulse techniques to determine longitudinal and lateral dynamic stability characteristics of the D-558-II research airplane with particular reference to the jet exhaust effects of the rocket engine. Results regarding the longitudinal stability characteristics, and lateral stability characteristics are provided.
Date: August 23, 1957
Creator: Wolowicz, Chester H. & Rediess, Herman A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of wing warp on the lift, drag, and static longitudinal stability characteristics of an aircraft configuration having an arrow wing of aspect ratio 1.86 at Mach numbers from 1.1 to 1.7

Description: Report presenting the results of a free-flight investigation to determine the effect of wing warp on the lift, drag, and static longitudinal stability characteristics of a low-drag aircraft with an arrow wing of aspect ratio 1.86. Results regarding the trim, drag, lift-drag ratios, and normal force and pitching moment are provided.
Date: August 30, 1957
Creator: Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory Investigation of Transpiration Cooling of a 40 Degree Double Wedge Using Nitrogen and Helium as Coolants at Stagnation Temperatures of 1,295 to 2,910 Degrees F

Description: Report presenting an investigation of transpiration cooling in a preflight jet model consisting of a double wedge of 40 degrees included angle with a porous stainless-steel specimen inserted flush with the top surface of the wedge. Nitrogen and helium were used as coolants and testing was conducted for flow rates ranging from about 0.03 to 0.30 percent of the local weight flow. The helium coolant required only about one-fourth to one-fifth the coolant flow weight as the nitrogen coolant for the… more
Date: August 1, 1957
Creator: Rashis, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of a Liquid Hydrogen Fuel System

Description: Memorandum presenting testing of a twin-engine light bomber modified to utilize hydrogen fuel in one of the two engines during flight at an altitude of 50,000 feet. Three completely successful flights were made using hydrogen fuel. Data are presented to show the effect of tank agitation on fuel pressure and fuel losses.
Date: August 19, 1957
Creator: Mulholland, Donald R.; Acker, Loren W.; Christenson, Harold H. & Gough, William V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Aerodynamic-Heating Data to a Mach Number of 15.5 on a Blunted Conical Nose With a Total Angle of 29 Degrees

Description: Report presenting testing of a five-stage rocket-propelled model flown to a Mach number of 15.5 and an altitude of 98,200 feet. Temperatures were measured at six stations along the inside surface of the blunted conical nose with a total angle of 29 degrees. Experimental and theoretical values were similar at the first temperature measuring station, but the experimental results became increasingly greater than the theoretical values at rearward measuring stations.
Date: August 1, 1957
Creator: Bland, William M., Jr.; Rumsey, Charles B.; Lee, Dorothy B. & Kolenkiewicz, Ronald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration

Description: Report discussing a model of a delta-wing configuration with four engines mounted two to a nacelle below the wing that was tested a variety of Mach numbers and Reynolds numbers. The wing static-pressure coefficients, wing pressure coefficients, and lift coefficient of different configurations are described.
Date: August 16, 1957
Creator: Falanga, Ralph A. & Judd, Joseph H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight investigation at transonic speeds of the power-on characteristics including some effects of sonic propulsive jets of a four-engine delta-wing configuration

Description: Report presenting an investigation of a free-flight model of a delta-wing configuration with four engines mounted two to a nacelle below the wing with rocket turbojet simulators operating at a range of Mach numbers. Results regarding wing pressure coefficients, fuselage pressure coefficient, airplane aerodynamic characteristics, and airplane trim are provided.
Date: August 16, 1957
Creator: Judd, Joseph H. & Falanga, Ralph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight investigation of comparative zero-lift rolling effectiveness of a leading edge and a trailing edge air-jet spoiler on an unswept wing

Description: Report presenting a free-flight investigation of the zero-lift rolling effectiveness of air-jet spoilers on an unswept flexible wing over a range of Mach numbers. Testing was made to determine the relative effectiveness of air-jet spoilers at leading-edge and trailing-edge locations. The leading-edge jet spoiler exhibited near-zero effectiveness at transonic speeds and had a roll reversal between Mach numbers 0.93 and 1.35.
Date: August 1, 1957
Creator: Kehlet, Alan B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight investigation of jet effects at low supersonic Mach numbers on a fighter-type configuration employing a tail-boom assembly: longitudinal stability and trim

Description: Report presenting flight tests over a range of Mach numbers to study the effects of a simulated afterburning turbojet engine on the gross longitudinal flight characteristics of two geometrically identical models of a swept-wing fighter-type configuration. Results regarding the trim characteristics, lift, pitching moment, dynamic stability, and drag are provided.
Date: August 30, 1957
Creator: Jackson, Bruce G. & Crabill, Norman L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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