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Comparisons of Shock Noise Predictions with Flight DataA flight test was performed at NASA Dryden Research Center in November 1991 utilizing both F18 and Fl6 aircraft. These flights were designed to provide (1) acoustic data that could be extrapolated to that of an HSCT at various points of its climb-to-cruise operation and (2) a data base for noise from a supersonic jet exhausting from an aircraft moving at high subsonic speeds. This presentation utilizes data obtained from these flyovers to evaluate predictions of broadband shock noise from supersonic jets in flight. The Fl8 is particularly suitable for flyovers of shock noise since it can be flown with one engine at flight idle. The second engine can then be operated at a pressure high enough to produce a supersonic nozzle exhaust and still maintain an unaccelerated, level flyover.
Document ID
19990110635
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Norum, T. D. (NASA Langley Research Center Hampton, VA United States)
Golub, R. A. (NASA Langley Research Center Hampton, VA United States)
Willshire, W. L. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
August 19, 2013
Publication Date
September 1, 1999
Publication Information
Publication: First NASA/Industry High Speed Research Program Nozzle Symposium
Subject Category
Acoustics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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