Accession Number:

AD0648501

Title:

AN EVALUATION OF THE HEIGHT VELOCITY DIAGRAM OF A HEAVYWEIGHT, HIGH ROTOR INERTIA, SINGLE ENGINE HELICOPTER

Descriptive Note:

Technical rept.

Corporate Author:

FEDERAL AVIATION ADMINISTRATION WASHINGTON DC AIRCRAFT DEVELOPMENT SERVICE

Personal Author(s):

• Hanley, William J.
• DeVore, Gilbert
• Martin, Shirrel

Report Date:

1966-11-01

Pagination or Media Count:

59.0

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 andor 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.

Descriptors:

• *HELICOPTERS
• VELOCITY
• FLIGHT TESTING
• INERTIA
• PERFORMANCE(ENGINEERING)
• LOADS(FORCES)
• HELICOPTER ROTORS
• WEIGHT
• ALTITUDE

Subject Categories:

• Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE