National Advisory Committee for Aeronautics (NACA) - 231 Matching Results

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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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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
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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
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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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Analysis of Limitations Imposed on One-Spool Turbojet-Engine Designs by Turbines Having Downstream Stators at 0, 2.0, and 2.8 Flight Mach Numbers

Description: Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limita… more
Date: January 19, 1955
Creator: Cavicchi, Richard H. & Constantine, Anita B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of a Nuclear Powered Supercritical-Water Cycle for Aircraft Propulsion

Description: Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.
Date: January 19, 1953
Creator: Karp, Irving M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds

Description: Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuse… more
Date: February 19, 1957
Creator: Syvertson, Clarence A.; Wong, Thomas J. & Gloria, Hermilo R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Roll Effectiveness of a Differentially Deflected Horizontal-Tail Surface on a 42 Degree Swept-Wing Model

Description: Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: June 19, 1956
Creator: Boisseau, Peter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Porous Gas-Heated Leading-Edge Section for Icing Protection of a Delta Wing

Description: "A tip section of a delta wing having an NACA 0004-65 airfoil section and a 600 leading-edge sweepback was equipped with a porous leading-edge section through which hot gas was bled for anti-icing. Heating rates for anti-icing were determined for a wide range of icing conditions. The effects of gas flow through the porous leading-edge section on airfoil pressure distribution and drag in dry air were investigated" (p. 1).
Date: January 19, 1955
Creator: Bowden, Dean T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power

Description: Report discussing the boundary-layer transition and heat-transfer measurements for a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. Boundary-layer transition was observed on the nose of the missile. The drag coefficient for a variety of Mach numbers was also obtained.
Date: December 19, 1957
Creator: Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Radiant Heat Transfer From Flames in a Single Tubular Turbojet Combuctor

Description: Memorandum presenting an investigation to determine the energy transfer by thermal radiation from the flame of a single tubular turbojet-engine combustor to the combustor liner. The effects of variations in combustor inlet-air pressure, fuel-air ratio, and air mass flow on the transfer of radiant energy were studied.
Date: August 19, 1952
Creator: Topper, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling Characteristics of a Transpiration-Cooled Afterburner With a Porous Wall of Brazed and Rolled Wire Cloth

Description: Memorandum presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratio of cooling air to combustion gas, and pressure altitudes. Maximum wall temperatures based on the cooling correlation were determined for a porous wall of uniform permeability at sea-level takeoff and for several flight Mach numbers. Results regarding typical data, cooling correlation, transpirati… more
Date: August 19, 1954
Creator: Koffel, William K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Descent Characteristics of Bodies of Revolution Simulating Anti-Personnel Bombs

Description: "An investigation has been conducted in the Langley 20-foot free spinning tunnel to study the relative behavior in descent of a number of homogeneous balsa bodies of revolution simulating anti-personnel bombs with a small cylindrical exploding device suspended approximately 10 feet below the bomb. The bodies of revolution included hemispherical, near-hemispherical, and near-paraboloid shapes. The ordinates of one near-paraboloid shape were specified by the Office of the Chief of Ordnance, U. S.… more
Date: December 19, 1951
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparative Study of Turbofan and Turbojet Engines

Description: Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.
Date: July 19, 1957
Creator: Kaufman, Harold R.; Benser, William A. & Gabriel, David S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane

Description: Report presenting an investigation of a model of the Convair B-58 airplane weapons system in the transonic tunnel for a range of Mach and Reynolds numbers. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.
Date: October 19, 1956
Creator: Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurement and Analysis of Turbulent Flow Containing Periodic Flow Fluctuations

Description: Memorandum presenting techniques for the measurement of the energy spectrum of flow fluctuations in both axial and lateral flow directions. A simple spectrum analysis is presented by which quantitative distinction may be made between turbulence and the flow disturbances associated with sound waves in ducts. Results regarding the measurement and analysis of turbulent-flow fields containing random and periodic flow fluctuations, effect of random sound disturbances on turbulence spectrum, and effe… more
Date: August 19, 1953
Creator: Mickelsen, William R. & Laurence, James C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Summary of Flight Data Obtained From 0.12-Scale Rocket-Powered Models of the Chance Vought Regulus 2 Missile

Description: Report discussing the longitudinal static and dynamic stability, overall duct performance, drag, and some static and dynamic lateral-stability data obtained from testing of the Chance Vought Regulus II missile. Five different models with various modifications were used in the investigation.
Date: August 19, 1958
Creator: Wineman, Andrew R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Rocket Engine Starting With Mixed Oxides of Nitrogen and Liquid Ammonia by Flow-Line Additives

Description: Memorandum presenting an investigation of the starting characteristics of mixed oxides of nitrogen - liquid ammonia rocket engines with light metal additives in the ammonia flow line for ignition. The oxidant consisted of 70 percent by weight nitrogen tetroxide and 30 percent nitric oxide. Results regarding the ignition experiments with 100-pound-thrust engine, 1000-pound-thrust engine experiments, and low-temperature experiments are provided.
Date: August 19, 1953
Creator: Kinney, George R.; Humphrey, Jack C. & Hennings, Glen
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation at Low Speed of the Spin Instability of Mortar-Shell Tails

Description: An investigation was made in the Langley stability tunnel to study the influence of number of fins, fin shrouding, and fin aspect ratio on the spin instability of mortar-shell tail surfaces. It was found that the 12-fin tails tested spun less rapidly throughout the angle-of-yaw range than did the 6-fin tails and that fin shrouding reduced the spin encountered by a large amount.
Date: June 19, 1957
Creator: Bird, John D. & Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method for Prevention of Screaming in Rocket Engines

Description: From Summary: "Lateral and longitudinal combustion-pressure oscillations that occurred in screaming combustion of a 1000-pound-thrust rocket engine using white fuming nitric acid and JP-4 fuel as propellants were successfully prevented by means of longitudinal fins in the combustion chamber. Fin position was critical, and complete attenuation was achieved only when the fins were located in a zone approximately 8 to 16 inches from the injector. Fins located in other zones, that is, near the inje… more
Date: August 19, 1954
Creator: Male, Theodore & Kerslake, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of a 28-Inch Ramjet Utilizing Gaseous Hydrogen at a Mach Number of 3.6, Angles of Attack Up to 12 Degrees, and Pressure Altitudes Up to 110,000 Feet

Description: Memorandum presenting an investigation conducted in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results of the investigation showed that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to … more
Date: May 19, 1958
Creator: Musial, Norman T.; Ward, James J. & Wasserbauer, Joseph F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Effects of Roll Rate on the Longitudinal Stability Characteristics of a Cruciform Missile Configuration as Determined From Flight Test for a Mach Number Range of 1.1 to 1.8

Description: Report discussing testing of a cruciform missile with a low-aspect-ratio wing and flap-type controls to determine the stability and control characteristics while rolling. Longitudinal stability and control effectiveness for this particular configuration were examined. The data obtained was compared to results from a similar model that was rolling significantly less.
Date: June 19, 1956
Creator: Lundstrom, Reginald R. & Baber, Hal T., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation of the Full-Scale Hughes Falcon Missile, D Configuration, to Determine Aileron Effectiveness and Damping in Roll

Description: Report discussing an investigation to determine the aileron effectiveness and damping in roll of the Hughes Falcon missile, D configuration at several Mach numbers. Information about the rolling-moment coefficient, damping-in-roll derivative, and drag coefficient is provided.
Date: November 19, 1954
Creator: Lundstrom, Reginald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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