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Approach and landing test supplemental reportTail-cone-off tests of the Shuttle Orbiter during the approach and landing phase are described with attention to attack angle during descent. Angles of from 2.5 to 16.5 deg were attempted with varying speed brake configurations in order to analyze stability and control for runway landings.
Document ID
19780044557
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Engle, J. H. (USAF Washington, D.C., United States)
Truly, R. H. (NASA Johnson Space Center Houston, Tex., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Space Transportation
Accession Number
78A28466
Distribution Limits
Public
Copyright
Other

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