Calculating procedure of sea-level static performance of two-spool afterburning bypass jet engine
By: by M.H. Vavra
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1973
Place of publication: Monterey, California
Language: eng
Number of pages: 106
Subjects: Fluid dynamics; Computer programs; Compressors; Aerodynamics; Jet propulsion; Turbomachines
Description: A calculating procedure is presented for the sea-level static performance of duct burning and afterburning bypass jet engines that have a low pressure and a high pressure spool.  Performance values can be determined also for operation without reheat.  Influence of temperature and fuel/air ratio on the thermodynamic properties of air and combustion gases is taken into account.  A calculating program for a Monroe 1880-43 programmable electronic desk calculator is described which makes it possible to evaluate effects of changes of parameters on performance with minimum effort.  The program will be used to establish the characteristics of compressors required for propulsive units of later generation Navy air-superiority fighter aircraft, to investigate whether the Turbo-Propulsion Laboratory of NPS would be capable of undertaking research and development work of such machines.  Programs of the type presented, and the use of modern programmable desk calculators, will also be of great value for instructional purposes.  Teachers can then concentrate on the fundamental nature of particular topics and need not waste time on lengthy derivations, or on simplifications and approximations that are introduced only to solve equations with elementary means.  The students would be relieved of the drudgery of routine hand calculations that do not contribute to a better understanding of the subject matter. (Author)
Notes: Title from cover.

"June 1973"--Cover.

"NPS-57VA73061A"--Cover.

Author(s) subject terms: Jet engine SLS performance prediction, bypass engine, after and duct burning engine, real gas effects, jet engine diameter for specified thrust.

"Approved for public release; distribution unlimited"--Cover.

Technical report; 1973.