Programme of Research into the Aerodynamics, Stability and Control Characteristics of a Combat Aircraft Having a Forward Swept Wing

摘要

The aerodynamic stability and control characteristics of the forward swept wing aircraft, and likely stability augmentation requirements were studied. It is found that: (1) the theoretical aerodynamic models match the observed aerodynamic performance; (2) the estimated stability derivatives when incorporated in a computer simulation provide response characteristics which agree with experimentally derived responses; (3) the parametric identification technique is effective; (4) theoretical predictions of longitudinal static stability margins indicate that the aircraft is more stable than observed in experiments; (5) feedback control is relatively straightforward; and (6) the experimental system permits dynamic testing on the aircraft model with a longitudinal static stability margin as small as -4%.