Description: Report presenting information about the acoustical near field produced by the exhaust of a stationary turbojet engine with a high pressure ratio measured for a single operating condition without afterburning. Additional testing was made at a few points to determine the difference in value between sound-pressure levels at rigid surfaces and corresponding free-field values. Results regarding overall sound pressure, sound-pressure level in frequency bands, sound-pressure-level spectra along jet boundary, and second-source noise are provided.
Date: October 1956
Creator: Howes, Walton L. & Mull, Harold R.
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Partner: UNT Libraries Government Documents Department