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Preliminary Altitude Performance Data for the J71-A2 (X-26) Turbojet Engine

Authors
  • Mallett, William E.
  • Useller, James W.
Publication Date
Aug 19, 1954
Source
NASA Technical Reports Server
Keywords
License
Unknown

Abstract

Data were obtained in an altitude test chamber for a range of altitudes from 20,000 to 58,000 feet at a flight Mach number of 0.9, and for several flight Mach numbers at an altitude of 45,000 feet. Data approximating sea-level operation are also included. Engine component performance data are presented in addition to windmilling, exhaust-nozzle, and ejector performance.

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