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An Optimal Deconvolution Method for Reconstructing Pneumatically Distorted Near-Field Sonic Boom Pressure MeasurementsIn-flight measurements of the SR-71 near-field sonic boom were obtained by an F-16XL airplane at flightpath separation distances from 40 to 740 ft. Twenty-two signatures were obtained from Mach 1.60 to Mach 1.84 and altitudes from 47,600 to 49,150 ft. The shock wave signatures were measured by the total and static sensors on the F-16XL noseboo. These near-field signature measurements were distorted by pneumatic attenuation in the pitot-static sensors and accounting for their effects using optimal deconvolution. Measurement system magnitude and phase characteristics were determined from ground-based step-response tests and extrapolated to flight conditions using analytical models. Deconvolution was implemented using Fourier transform methods. Comparisons of the shock wave signatures reconstructed from the total and static pressure data are presented. The good agreement achieved gives confidence of the quality of the reconstruction analysis. although originally developed to reconstruct the sonic boom signatures from SR-71 sonic boom flight tests, the methods presented here generally apply to other types of highly attenuated or distorted pneumatic measurements.
Document ID
Document Type
Technical Publication (TP)
Whitmore, Stephen A. (NASA Dryden Flight Research Center Edwards, CA, United States)
Haering, Edward A., Jr. (NASA Dryden Flight Research Center Edwards, CA, United States)
Ehernberger, L. J. (NASA Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
August 24, 2013
Publication Date
June 1, 1996
Subject Category
Aircraft Design, Testing and Performance
Report/Patent Number
NASA TP-4000
Funding Number(s)
WORK_UNIT: WU 505-37-03
Distribution Limits
Work of the US Gov. Public Use Permitted.

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