Stability and control flight tests were conducted on the OH-4A helicopter to determine the stability and control characteristics throughout the flight envelope for the unarmed (clean) and armed configurations. Ninety-three test flights were conducted for 75:30 hours productive test time. All test data were hand recorded from sensitive instruments or recorded on an oscillograph. The quantitative test results and qualitative pilot's comments indicate that the OH-4A complied with most of the stability and control requirements of MIL-H-8501A.
Report of the Engineering Flight Test -- Stability and Control Phase -- of the OH-4A Helicopter, Unarmed (Clean) and Armed with the XM-7 or XM-8 Weapon Subsystem. Part I
1964
323 pages
Report
Keine Angabe
Englisch
Aircraft , Helicopters , Flight testing , Stability , Pitch(Motion) , Yaw , Roll , Flight control systems , Handling , Pilots , Performance(Human) , Response , Aerodynamic configurations , Aircraft guns , Grenades , Firing tests(Ordnance) , Vibration , Flight speeds , Level flight , Hovering , Climbing , Takeoff , Aircraft landings , Weight , Center of gravity , Angle of attack , Graphics , Oh-4a aircraft , H-4 aircraft , Lightweight , Observation aircraft , Loh(Light observation helicopters) , M-60c guns(7.62-mm) , M-60 guns(7.62-mm) , M-7 weapon systems , M-75 grenade launchers(40-mm) , M-8 weapon systems , Xm-7 weapon systems , Xm-8 weapon systems