A series of flight tests was conducted at three selected altitudes (sea level, 5000 feet, 6500 feet) to determine the effects of altitude and weight on the height-velocity (H-V) diagram of a large, heavyweight, high rotor inertia, high disk loading, single rotor, single engine helicopter. Three gross weights of the helicopter were used. Quantitative and qualitative test data were collected to determine how the H-V diagram varies with density altitude and aircraft gross weight. An investigation was made into the effects on the diagram of a delayed collective pitch application response. Results disclosed a family of curves showing that increases in density altitude and/or gross weight enlarged the H-V diagram required for a safe power-off landing. Analysis of the results revealed that the key points (V sub cr, h sub min, and h sub max), which partially define the curves, could be determined by the solution of a set of linear equations. (Author)
An Evaluation of the Height Velocity Diagram of a Heavyweight, High Rotor Inertia, Single Engine Helicopter
1966
68 pages
Report
Keine Angabe
Englisch