AN EVALUATION OF THE HEIGHT VELOCITY DIAGRAM OF A HEAVYWEIGHT, HIGH ROTOR INERTIA, SINGLE ENGINE HELICOPTER
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1966
- Accession Number
- AD0648501
Entities
People
- Gilbert Devore
- Shirrel Martin
- William J. Hanley
Organizations
- Federal Aviation Administration