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
Flight angle of attack determined from ablative heat-shield patterns.Hypersonic trim angle of attack of lifting entry vehicles, correlating stagnation point values obtained from heat shield ablation and pressure distribution measurements
Document ID
19670050718
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Whitnah, A. M.
Date Acquired
August 3, 2013
Publication Date
June 1, 1967
Publication Information
Publication: JOURNAL OF SPACECRAFT AND ROCKETS
Subject Category
Aerodynamics
Accession Number
67A29447
Distribution Limits
Public
Copyright
Other
Keywords
PRESSURE DISTRIBUTION
HEAT SHIELD
AERODYNAMIC HEATING
HYPERSONIC SPEED
ANGLE OF ATTACK
STAGNATION POINT

Available Downloads

There are no available downloads for this record.

Related Records

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