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Fuselage design for a specified Mach-sliced area distributionA procedure for designing a fuselage having a prescribed effective area distribution computed from -90 deg Mach slices is described. This type of calculation is an essential tool in designing a complete configuration with an effective area distribution that corresponds to a desired sonic boom signature shape. Sample calculations are given for M=2 and M=3 designs. The examples include fuselages constrained to have circular cross sections and fuselages having cross sections of arbitrary shape. It is found that, for a prescribed effective area distribution having sharp variations, the iterative procedure converges to a smoothed approximation to the prescribed distribution. For a smooth prescribed area distribution, the solution is not unique.
Document ID
19900009069
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Barger, Raymond L. (NASA Langley Research Center Hampton, VA, United States)
Adams, Mary S. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1990
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.60:2975
NASA-TP-2975
L-16651
Accession Number
90N18385
Funding Number(s)
PROJECT: RTOP 505-60-01-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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