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Locally linearized longitudinal and lateral-directional aerodynamic stability and control derivaties for the X-29A aircraftThe locally linearized longitudinal and lateral-directional aerodynamic stability and control derivatives for the X-29A aircraft were calculated for altitudes ranging from sea level to 50,000 ft, Mach numbers from 0.2 to 1.5, and angles of attack from -5 deg to 25 deg. Several other parameters were also calculated, including aerodynamic force and moment coefficients, control face position, normal acceleration, static margin, and reference angle of attack.
Document ID
19860014095
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Budd, G. D. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:84919
H-1203
NASA-TM-84919
Accession Number
86N23566
Funding Number(s)
PROJECT: RTOP 533-02-81
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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