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Formulation of a General Technique for Predicting Pneumatic Attenuation Errors in Airborne Pressure Sensing DevicesPresented is a mathematical model derived from the Navier-Stokes equations of momentum and continuity, which may be accurately used to predict the behavior of conventionally mounted pneumatic sensing systems subject to arbitrary pressure inputs. Numerical techniques for solving the general model are developed. Both step and frequency response lab tests were performed. These data are compared with solutions of the mathematical model and show excellent agreement. The procedures used to obtain the lab data are described. In-flight step and frequency response data were obtained. Comparisons with numerical solutions of the math model show good agreement. Procedures used to obtain the flight data are described. Difficulties encountered with obtaining the flight data are discussed.
Document ID
19880010918
Acquisition Source
Headquarters
Document Type
Technical Memorandum (TM)
Authors
Whitmore, Stephen A. (NASA Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1988
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:100430
H-1462
NASA-TM-100430
Accession Number
88N20302
Funding Number(s)
PROJECT: RTOP 505-68-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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