An investigation was made at transonic speeds to determine some of the dynamic stability derivatives of a 45 deg. sweptback-wing airplane model. The model was sting mounted and was rigidly forced to perform a single-degree-of-freedom angular oscillation in pitch or yaw of +/- 2 deg. The investigation was made for angles of attack alpha, from -4 deg. to 14 deg. throughout most of the transonic speed range for values of reduced-frequency parameter from 0.015 to 0.040 based on wing mean aerodynamic chord and from 0.04 to 0.14 based on wing span. The results show that reduced frequency had only a small effect on the damping-in-pitch derivative and the oscillatory longitudinal stability derivative for all Mach numbers M and angles of attack with the exception of the values of damping coefficient near M = 1.03 and alpha = 8 deg. to 14 deg.
Dynamic Longitudinal and Directional Stability Derivatives for a 45 deg. Sweptback-Wing Airplane Model at Transonic Speeds
1959
54 pages
Report
No indication
English
Aerodynamics , Aircraft , Aircraft models , Directional stability , Longitudinal stability , Transonic speed , Wind tunnel tests , Sweptback wings , Aerodynamic configurations , Aircraft control , Angle of attack , Chords(Geometry) , Mach number , Frequencies , Pitch(Inclination) , Tail assemblies , Yaw , Wing span