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Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination

Description: Report presenting tests of an airplane model equipped with missiles to investigate the capability of that combination to achieve satisfactory launching and jettisoning of the missiles. Information about pylon modifications, missiles in launch positions, missile trajectory, and missiles in jettison positions is provided.
Date: November 20, 1957
Creator: Cleary, Joseph W.; Frank, Joseph L. & Dewey, C. Forbes, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model

Description: Memorandum presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.
Date: May 26, 1958
Creator: Matthews, Clarence W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Effects of Aileron Deflection on the Static Lateral and Directional Aerodynamic Characteristics of Four Contemporary Airplane Models

Description: Memorandum presenting some effects of aileron deflection on the static lateral and directional aerodynamic characteristics of four airplane models which are representative of aircraft capable of flight at supersonic speeds. The results are presented for subsonic Mach numbers ranging from 0.60 to 0.90 and for supersonic Mach numbers ranging from 1.20 to 1.90. They are limited to the most pertinent aerodynamic effects of ailerons contributing to the lateral and directional characteristics of each… more
Date: July 23, 1957
Creator: Smith, Willard G. & Intrieri, Peter F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines

Description: Report discussing performance estimates for several airplanes using General Electric AC-210 ramjet nuclear-powered engines. Assumptions used for designing the engines, radiation shield, and airframe are described. Potential tradeoffs in regards to power and weight reduction are also discussed.
Date: April 11, 1958
Creator: Weber, Richard J. & Connolley, Donald J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

Description: Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale … more
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turbine Failure Investigation of J65-W-4 Turbojet Engine in an Altitude Test Chamber

Description: Memorandum presenting an altitude investigation to determine the basic mechanism by which J65-W-4 turbine rotor-blade failures were occurring in service. The engine was installed in an altitude test chamber and a series of controlled engine throttle bursts, with and without inlet-air distortion, over a range of altitudes, flight Mach numbers, and inlet-air temperatures. An examination of the data obtained during the investigation indicated that the danger of turbine failure could be eliminated … more
Date: September 21, 1956
Creator: McAulay, John E.; Braithwaite, Willis M. & Ciepluch, Carl C.
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
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Hydrodynamic Characteristics of Missiles Launched Under Water

Description: Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.
Date: June 27, 1958
Creator: Dawson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Preliminary Investigation of the Performance of a Short Length Turbojet Combustor Using Vaporized Hydrocarbon Fuels

Description: "Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one-quarter annular duct. The experimental combustors consisted of many small "swirl-can" combustor elements manifolded together. This design approach allowed the secondary mixing zone to be considerably reduced over that of conventional combustors" (p. 1).
Date: January 7, 1958
Creator: Jones, R. E. & Pawlik, E. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat-Exchanger-Core Weights for Use With Hydrogen-Expansion Turbine

Description: Memorandum presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. This is because rotary regenerators offer possibilities for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.
Date: October 3, 1957
Creator: Reynolds, Thaine W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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
open access

Hydrogen for Turbojet and Ramjet Powered Flight

Description: Memorandum presenting various reports regarding the use of hydrogen for turbojet and ramjet powered flight. Some of the characteristics considered include the combustion properties, potential fueling problems, and flight experience with hydrogen on-board.
Date: April 26, 1957
Creator: Lewis Flight Propulsion Laboratory
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels

Description: Memorandum presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet, and the ultimate blowout limit was at an altitude of about 75,000 feet. The steady-state performance with either fuel decreased considerably with increasing altitude.
Date: April 2, 1957
Creator: Kaufman, Harold R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of turbojet and ram-jet engine cycles using various fuels

Description: From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date: November 27, 1956
Creator: Wilcox, E. Clinton; Weber, Richard J. & Tower, Leonard K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Diffuser Pressure Ratio Control With Shock Positioning Limit on 28 Inch Ram-Jet Engine

Description: Report presenting an investigation of the performance of a diffuser static-pressure-ratio control with a normal shock-positioning limit on a ramjet engine installed in an altitude free-jet facility. Testing occurred at Mach numbers of 2.35 and 2.50, altitudes of 50,000, 60,000 and 65,000 feet, and angles of attack of 0 and 7 degrees. Results regarding the effects of control constants, effects of disturbance size and operating point, effects of flight conditions, and control limitations and poss… more
Date: January 15, 1957
Creator: Dunbar, William R.; Wentworth, Carl B. & Crowl, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Evaluation of Swirl Can Elements for Hydrogen Fuel Combustor

Description: Memorandum presenting a study of the performance of swirl-can combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential, sonic orifice that created a swirling fuel-air mixture within each element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of multielement combustor are provided.
Date: May 13, 1957
Creator: Rayle, Warren D.; Jones, Robert E. & Friedman, Robert
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 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

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
open access

NACA Conference on High-Speed Aerodynamics: A Compilation of Papers Presented

Description: A reproduction of the technical papers presented by staff members of the NACA Laboratories at the NACA Conference on High-Speed Aerodynamics at the Ames Aeronautical Laboratory during March 18-20, 1958. The primary purpose of the conference was to convey to military services and contractors the results of recent research and to provide an opportunity to discuss the results.
Date: 1958-03-18/1958-03-20
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

NACA Conference on Aircraft Loads, Structures, and Flutter

Description: "This document contains reproductions of technical papers on some of the most recent research results on aircraft loads, flutter, and structures from the NACA laboratories. These papers were presented by members of the staff of the NACA laboratories at the Conference held at the Langley Aeronautical Laboratory March 5, 6, and 7, 1957. The primary purpose of this Conference was to convey to contractors of the military services and others concerned with the design of aircraft these recent researc… more
Date: March 5, 1957
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigations on Reductions of Friction on Wings, in Particular by Means of Boundary Layer Suction

Description: Memorandum presenting investigation on reductions of friction on wings, especially by means of boundary-layer suction. The report is broken up into several sections, including: causes of transition, laminar profiles with the transition taking place, laminar boundary-layer suction, investigation of the laminar pressure increase, investigation of the slot flow for laminar boundary-layer suction with single slots, tests about keeping a boundary layer for high Reynolds laminar with the aid of bound… more
Date: August 1947
Creator: Pfenninger, Werner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigations Relating to the Extension of Laminar Flow by Means of Boundary-Layer Suction Through Slots

Description: Note presenting experimental investigations of boundary-layer suction through slots as a means of increasing the extent of laminar flow on airfoil sections. The results show that, with the use of suitable slots, substantial increases in the extent of laminar flow can be achieved by boundary-layer control with only a small expenditure of power. Results regarding slot geometry and arrangement, suction slots in an unfavorable pressure gradient, suction slots in a favorable pressure gradient, and d… more
Date: October 1949
Creator: Loftin, Laurence K., Jr. & Burrows, Dale L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of the Profile Drag of an Airplane Wing in Flight at High Reynolds Numbers

Description: Report presenting flight tests to determine the profile-drag coefficients of a portion of the original wing surface of an all-metal airplane and a portion of the wing made aerodynamically smooth and more nearly fair than the original section. Tests were also carried out to determine the point of transition from laminar to turbulent boundary layer and to determine the velocity distribution along the upper surface of the wing.
Date: 1939
Creator: Bicknell, Joseph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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