Experimental and predicted longitudinal and lateral-directional response characteristics of a large flexible 35 degree swept-wing airplane at an altitude of 35,000 feet

Henry A. Cole, Jr., Stuart C. Brown, Euclid C. Holleman
naca-report-1330
Jan 1957


Measured and predicted dynamic response characteristics of a large flexible swept-wing airplane to control surface inputs are presented for flight conditions of 0.6 to 0.85 Mach number at an altitude of 35,000 feet. The report is divided into two parts. The first part deals with the response of the airplane to elevator control inputs with principal responses contained in a band of frequencies including the longitudinal short-period mode and several symmetrical structural modes. The second part deals with the response of the airplane to aileron and rudder control inputs with principal responses contained in a band of frequencies including the dutch roll mode, the rolling mode, and three antisymmetrical structural modes.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1957/naca-report-1330.pdf