NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
Including re-entry heating in rocket engine thermal analyses.Reentry heat flux condition transformation into specified convective coefficients and temperatures, accounting for variation of flux with wall temperature
Document ID
19660063505
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Fineman, S.
Glick, R. L.
Date Acquired
August 3, 2013
Publication Date
October 1, 1966
Subject Category
Propulsion Systems
Accession Number
66A42795
Funding Number(s)
CONTRACT_GRANT: NAS8-14022
Distribution Limits
Public
Copyright
Other
Keywords
REENTRY CONDITION
CONVECTIVE HEAT TRANSFER
HEAT FLUX
WALL TEMPERATURE
APPROXIMATION METHOD

Available Downloads

There are no available downloads for this record.

Related Records

There are no records associated with this record.
No Preview Available