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Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing
From Introduction: "The configuration described in this paper represents one approach to such an airplane and the results of the wind-tunnel and tank evaluations are presented. In the present investigation, the aerodynamic longitudinal characteristics over a Mach number range from 0.6 to 1.97 were obtained."
Date:
October 23, 1957
Creator:
Petynia, William W.; Hasson, Dennis F. & Spooner, Stanley H.
System:
The UNT Digital Library
Effect of Boundary Solidity of Planing Lift Obtained in a High-Speed Water Jet With a Single Longitudinal Slot in Each Rigid Boundary
Report discussing the hydrodynamic planing-lift forces of a model of a rectangular jet with several boundaries with slots in them in order to obtain varying boundary solidities. The lift coefficients at the different boundary solidities were compared to computed values from an equation. Information about the effects of boundary solidity, the level of optimum solidity, and the effects of speed is provided.
Date:
October 23, 1957
Creator:
Weinflash, Bernard
System:
The UNT Digital Library
Preliminary Indications of the Cooling Achieved by Ejecting Water Upstream From the Stagnation Point of Hemispherical, 80 Degree Conical, and Flat-Faced Nose Shapes at a Stagnation Temperature of 4,000 F
Memorandum presenting an investigation of the effectiveness of water-vaporization cooling that would be obtained by ejecting water upstream from the stagnation point conducted in a liquid-fuel rocket jet as a stagnation temperature of 4000 degrees Fahrenheit.
Date:
October 23, 1957
Creator:
Rashis, Bernard
System:
The UNT Digital Library
Two-dimensional cascade tests of NACA 65-(C(sub zeta)(sub o))A(sub 10))10 blade sections at typical compressor hub conditions for speeds up to choking
Report presenting two-dimensional porous-wall cascade tests of specified NACA blade sections at typical compressor hub conditions at speeds up to choking. For typical compressor blade hub sections, the angle of attack for best operation at high Mach numbers is about 6 degrees higher than the design angle of attack for low speeds. Results regarding the 65-series blade tests and circular-arc blade-section tests are provided.
Date:
October 23, 1957
Creator:
Emery, James C. & Dunavant, James C.
System:
The UNT Digital Library
Altitude evaluation of several afterburner design variables on a J47-GE-17 turbojet engine
From Introduction: "The investigation reported herein presents information on design factors and modifications of the production afterburner for the J47-GE-17 turbojet engine designed for medium temperature operation. The present report is concerned only with the afterburner performance and operating characteristics.Altitude-starting characteristics of two of the configurations in this report are discussed in reference 1."
Date:
October 23, 1953
Creator:
Braithwaite, Willis M.; Walker, Curtis L. & Sivo, Joseph N.
System:
The UNT Digital Library
Evaluation of ethyl ether as an ignition aid for turbojet engine fuels
Report presenting an investigation to determine the effectiveness of ethyl ether as an ignition aid for low-volatility turbojet-engine fuels. The minimum spark engines required to ignite a single J33 combustor over a range of altitude inlet-air pressures and flow rates with several fuel blends are provided.
Date:
October 23, 1953
Creator:
Jonash, Edmund R. & Foster, Hampton H.
System:
The UNT Digital Library
Performance comparison at supersonic speeds of inlets spilling excess flow by means of bow shock, conical shock, or bypass
Report presenting a comparison of fixed-geometry, translating-spike, and bypass-inlets on the basis of turbojet- and ramjet-engine performance. Results regarding a comparison of the experimental data and its application to ramjet and turbojet engines are provided.
Date:
October 23, 1953
Creator:
Allen, J. L. & Beke, Andrew
System:
The UNT Digital Library
Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system
The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.
Date:
October 23, 1951
Creator:
Armstrong, John C.
System:
The UNT Digital Library