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An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control
Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.
Date:
May 12, 1958
Creator:
Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
System:
The UNT Digital Library
An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control
Memorandum presenting an acceleration-limiting control used on a turbojet engine to study the feasibility of its use as an acceleration control. A proportional-plus-integral type of controller was used in this investigation. Results regarding one-loop control and two-loop control are provided.
Date:
May 12, 1958
Creator:
Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
System:
The UNT Digital Library
High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser
Low cowl drag, external compression inlet with subsonic dump diffuser for high Mach number application.
Date:
May 12, 1958
Creator:
Connors, James F. & Flaherty, Richard J.
System:
The UNT Digital Library
High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser
Report presenting an investigation of a zero-cowl-drag, all-external-compression inlet with an abrupt area discontinuity or subsonic dump diffuser for high Mach number application. Results regarding the diffuser performance characteristics, effect of spike retraction, a comparison with other inlets, and some theoretical calculations related to the results are provided.
Date:
May 12, 1958
Creator:
Connors, James F. & Flaherty, Richard J.
System:
The UNT Digital Library
Preliminary survey of possible methods for hypersonic aircraft
Report presenting an investigation conducted to determine the relative advantages and limitations of a number of fluids for use as either heat sinks or coolants for hypersonic aircraft. The feasibility of the fluids tested as heat sinks and cooling in the high-level and low-level regions is described.
Date:
May 12, 1958
Creator:
Esgar, Jack B.; Hickel, Robert O. & Stepka, Francis S.
System:
The UNT Digital Library
Theoretical Performance of Liquid Ammonia With Liquid Oxygen as a Rocket Propellant
Memorandum presenting theoretical rocket performance for both equilibrium and frozen composition during expansion, which was calculated for the propellant combination of liquid ammonia with liquid oxygen at two chamber pressures and a wide range of pressure ratios and oxidant-fuel ratios. Some of the performance parameters explored include specific impulse, specific impulse in vacuum, combustion-chamber temperature, nozzle-exit temperature, molecular weight, molecular-weight derivatives, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity, Mach number, and equilibrium gas compositions.
Date:
May 12, 1958
Creator:
Gordon, Sanford & Glueck, Alan R.
System:
The UNT Digital Library