Some Altitude Operational Characteristics of a Prototype Iroquois Turbojet Engine, COORD. NO. AF-P-6
Description: The evaluation of the altitude operational characteristics was part of the over-all investigation of the early developmental Iroquois engine. Engine steady-state windmilling characteristics were evaluated over a range of flight Mach numbers from 0.48 to 1.72 at altitudes of 35,000 and 50,000 feet. Engine altitude ignition limits were obtained over a range of flight Mach numbers from 0.5 to 1.5 with the standard engine ignition system and also with an oxygen boost system. A short investigation of high-speed altitude reignition following combustor blowout was conducted.
Date: June 17, 1958
Creator: Peters, Daniel J. & McAulay, John E.
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Partner: UNT Libraries Government Documents Department