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Study to define unsteady flow fields and their statistical characteristics

Author
Robertson, J. E.
Published
May 1, 1975.
Physical Description
1 electronic document
Additional Creators
Slone, R. M., Jr. and Wang, M. E.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
Preliminary estimates of space shuttle fluctuating pressure environments were made based on analyses of wind tunnel data, and empirical prediction techniques. Particular emphasis was given to the external tank and solid rocket boosters for the transonic speed regime during launch of a parallel-burn space shuttle configuration. Predicted environments are presented as space-averaged zonal profiles with progressive shading from zone to zone to illustrate spatial variations in the magnitude of the fluctuating pressure coefficient over the surfaces of the external tank and solid rocket boosters. Predictions are provided for the transonic Mach number range from 0.8 equal to or less than M sub infinity equal to or less than 1.5, and for supersonic Mach numbers of 2.0 and 3.0.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19760005933.
Accession ID: 76N13021.
NASA-CR-144092.
WR-75-1.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15737870