Publication Date:
2019-06-28
Description:
The 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.
Keywords:
AERODYNAMICS
Type:
NASA-TM-84919
,
H-1203
,
NAS 1.26:84919
Format:
application/pdf
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