Force and moment coefficients computed from test data are presented. Data indicate that, with respect to elevator-angle variation with speed, airplane will become unstable at approximately 0.7 Mach number. Two devices for improving longitudinal control, a wing-profile modification and auxiliary control flaps, increase the Mach number at which this instability occurs. Former device increases it by as much as 0.075 and 0.8 Mach number, their over- all characteristics are less favorable than those of wing-profile modification.
Longitudinal Characteristics and Aileron Effectiveness of a Midwing Airplane from High-Speed Wind-Tunnel Tests
1944
74 pages
Report
No indication
English
Engineering Index Backfile | 1944
|Wind tunnel tests on aileron loads
SLUB | 1932
|Wind tunnel tests on aileron loads
TIBKAT | 1932
|