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.
Locally Linearized Longitudinal and Lateral-Directional Aerodynamic Stability and Control Derivaties for the X-29A Aircraft
1984
480 pages
Report
Keine Angabe
Englisch