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Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination
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.
System:
The UNT Digital Library
Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model
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.
System:
The UNT Digital Library
Some Effects of Aileron Deflection on the Static Lateral and Directional Aerodynamic Characteristics of Four Contemporary Airplane Models
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 airplane type.
Date:
July 23, 1957
Creator:
Smith, Willard G. & Intrieri, Peter F.
System:
The UNT Digital Library
Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines
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.
System:
The UNT Digital Library
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
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 aircraft.
Date:
June 24, 1958
Creator:
Oehman, Waldo I. & Turner, Kenneth L.
System:
The UNT Digital Library
Turbine Failure Investigation of J65-W-4 Turbojet Engine in an Altitude Test Chamber
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 without any appreciable sacrifice in engine acceleration time.
Date:
September 21, 1956
Creator:
McAulay, John E.; Braithwaite, Willis M. & Ciepluch, Carl C.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
Hydrodynamic Characteristics of Missiles Launched Under Water
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.
System:
The UNT Digital Library
A Preliminary Investigation of the Performance of a Short Length Turbojet Combustor Using Vaporized Hydrocarbon Fuels
"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.
System:
The UNT Digital Library
Heat-Exchanger-Core Weights for Use With Hydrogen-Expansion Turbine
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.
System:
The UNT Digital Library
Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine
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.
System:
The UNT Digital Library
Hydrogen for Turbojet and Ramjet Powered Flight
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
System:
The UNT Digital Library
High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels
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.
System:
The UNT Digital Library
Analysis of turbojet and ram-jet engine cycles using various fuels
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.
System:
The UNT Digital Library
Experimental Investigation of Diffuser Pressure Ratio Control With Shock Positioning Limit on 28 Inch Ram-Jet Engine
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 possible improvements are provided.
Date:
January 15, 1957
Creator:
Dunbar, William R.; Wentworth, Carl B. & Crowl, Robert J.
System:
The UNT Digital Library
Experimental Evaluation of Swirl Can Elements for Hydrogen Fuel Combustor
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
System:
The UNT Digital Library
Design and performance of flight-type liquid-hydrogen heat exchanger
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.
System:
The UNT Digital Library
Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System
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.
System:
The UNT Digital Library
Flight Investigation of a Liquid Hydrogen Fuel System
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.
System:
The UNT Digital Library
Wind-Tunnel Investigation of a 1/60-Scale Model of the Republic MX-1554 Airplane at a Mach Number of 2.85
Report presenting the results of an investigation to determine the static longitudinal and lateral stability and control characteristics of a model of the Republic MX-1554 airplane at a specified Mach and Reynolds number. No analysis was provided in the paper in order to expedite publication.
Date:
March 18, 1953
Creator:
Dickey, Robert R. & Spahr, J. Richard
System:
The UNT Digital Library
Tracking Performance of a Swept-Wing Fighter With a Director-Type Radar Fire-Control System and Scope Presentation
Memorandum presenting flight tests conducted with an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracking performance in the manual mode of operation were investigated. Results regarding fixed-sight tracking and tracking with scope presentation are provided.
Date:
January 20, 1958
Creator:
Turner, Horward L.; Rathert, George A., Jr. & Heinle, Donovan R.
System:
The UNT Digital Library
A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance
Memorandum presenting flight tests conducted with a director-type radar fire-control system, with scope presentation of the steering information, to determine the effects of attack-display smoothing on the pilot's tracking and steering effectiveness in tail-chase and lead-collision beam attacks. Results regarding tail-chase attacks and lead-collision beam attacks are provided.
Date:
September 10, 1958
Creator:
Turner, Howard L. & Heinle, Donovan R.
System:
The UNT Digital Library
Thrust and Pumping Characteristics of a Series of Ejector-type Exhaust Nozzles at Subsonic and Supersonic Flight Speeds
Report presenting an investigation in the supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Results indicated that the free-stream Mach number had no effect on those characteristics of the ejectors in the range for which the secondary flow was choked.
Date:
November 17, 1954
Creator:
Hearth, Donald P. & Valerino, Alfred S.
System:
The UNT Digital Library
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
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 limitations.
Date:
January 19, 1955
Creator:
Cavicchi, Richard H. & Constantine, Anita B.
System:
The UNT Digital Library