A series of flight tests were conducted on the PC 9/A aircraft, A23- 045, at the Royal Australian Air Force's Aircraft Research and Development Unit. System identification techniques were applied to the data obtained from these flight tests to determine the stability and control derivatives of the aircraft. The lateral results for the aircraft in cruise configuration are presented in this report and comparisons are made with empirical and ground based estimates.
Correlation between Flight-determined Lateral Derivatives and Ground- based Data for the Pilatus PC 9/A Training Aircraft in Cruise Configuration
2000
59 pages
Report
No indication
English