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Internal performance of several types of jet-exit configurations for supersonic turbojet aircraft
Investigation of the internal performance characteristics of several jet-exit configurations over a wide range of pressure ratios, which are summarized to provide an overall picture of jet-exit performance. The configurations investigated include a convergent nozzle, fixed convergent-divergent nozzles, an adjustable plug-type convergent-divergent nozzle, and jet ejectors. Results regarding the performance of several jet-exit configurations and matching adjustable jet exits to supersonic aircraft are provided.
Date:
January 13, 1953
Creator:
Fleming, William A.
System:
The UNT Digital Library
Effect of liner air-entry holes, fuel state, and combustor size on performance of an annular turbojet combustor at low pressures and high air-flow rates
Report presenting the development of an annular combustor by utilizing the design principles evolved in previous investigations and by making 12 design changes to optimize the altitude performance of the combustor. Three types of fuels were used and the combustion efficiency, pressure losses, and outlet temperature profiles were evaluated.
Date:
January 13, 1953
Creator:
Norgren, Carl T. & Childs, J. Howard
System:
The UNT Digital Library
Stability and control characteristics at low speed of a 1/10-scale model of MX-1554A design
Report presenting an investigation of the low-speed stability and control characteristics of a scale model of the proposed MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. Results regarding the effect of wing incidence, tail position, fences, and chord extensions on the longitudinal characteristics are provided.
Date:
January 13, 1953
Creator:
Lockwood, Vernard E. & Solomon, Martin
System:
The UNT Digital Library
Determination of Mean Camber Surfaces for Wings Having Uniform Chordwise Loading and Arbitrary Spanwise Loading in Subsonic Flow
"The field of a uniformly loaded wing in subsonic flow is discussed in terms of the acceleration potential. It is shown that, for the design of such wings, the slope of the mean camber surface at any point can be determined by a line integration around the wing boundary. By an additional line integration around the wing boundary, this method is extended to include the case where the local section lift coefficient varies with spanwise location (the chordwise loading at every section still remaining uniform)" (p. 471).
Date:
January 13, 1953
Creator:
Katzoff, S.; Faison, M. Frances & DuBose, Hugh C.
System:
The UNT Digital Library
Effect of fuel volatility characteristics on ignition-energy requirements in a turbojet combustor
Report presenting an investigation to determine the effect of fuel volatility characteristics on the minimum spark energy required to ignite a single tubular turbojet-engine combustor. Results regarding the ignition at sea-level conditions, ignition at altitude conditions, relation between distillation data and minimum ignition-energy requirements, and application of relation to data from a previous investigation are provided.
Date:
January 13, 1953
Creator:
Foster, Hampton H. & Straight, David M.
System:
The UNT Digital Library