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Mach 6 experimental and theoretical stability and performance of a finned cylindrical body at angles of attack up to 65 degA theoretical and experimental investigation of the longitudinal and lateral-directional stability and control of a finned cylindrical body has been conducted at Mach 6. The angle-of-attack range extended from 20 to 65 deg. to encompass maximum lift. Stability, performance, and trim could be accurately predicted with the fins in the + arrangement but this was not the case when the fins were in the x orientation where windward fin choking occurred at angles of attack above 50 deg. reducing their effectiveness and causing pitch up.
Document ID
19870003105
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Hartman, E. R. (NASA Langley Research Center Hampton, VA, United States)
Johnston, P. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-89050
NAS 1.15:89050
Accession Number
87N12538
Funding Number(s)
PROJECT: RTOP 505-62-81-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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