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Computations for the 16-foot transonic tunnel, NASA, Langley Research Center, revision 1The equations used by the 16 foot transonic tunnel in the data reduction programs are presented in eight modules. Each module consists of equations necessary to achieve a specific purpose. These modules are categorized in the following groups: tunnel parameters; jet exhaust measurements; skin friction drag; balance loads and model attitudes calculations; internal drag (or exit-flow distributions); pressure coefficients and integrated forces; thrust removal options; and turboprop options. This document is a companion document to NASA TM-83186, A User's Guide to the Langley 16 Foot Transonic Tunnel, August 1981.
Document ID
19870010861
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mercer, Charles E. (NASA Langley Research Center Hampton, VA, United States)
Berrier, Bobby L. (NASA Langley Research Center Hampton, VA, United States)
Capone, Francis J. (NASA Langley Research Center Hampton, VA, United States)
Grayston, Alan M. (Wyle Labs., Inc. Hampton, Va., United States)
Sherman, C. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1987
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
NAS 1.15:86319-REV-1
NASA-TM-86319-REV-1
Accession Number
87N20294
Funding Number(s)
PROJECT: RTOP 505-62-91-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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