DETERMINATION OF THE RANGE PERFORMANCE OF A GAS TURBINE ENGINED HELICOPTER FROM FLIGHT TEST RESULTS
Abstract
After a simplified theoretical introduction, this report deals with methods of analyzing flight test results and planning a test programme to determine the range of a turbine engined helicopter and how it should be flown to achieve the greatest range. Results for a particular helicopter show that in standard atmospheric conditions the best range will normally be achieved when flying at the maximum permitted rotor speed and airspeed at an altitude which increases with decreasing weight but is, for normal operating weights, about 6,000 feet. There may be an appreciable loss of range if the wrong altitude is chosen. It is shown that a twin turbine helicopter may achieve its maximum range by flying on one engine.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 12, 1963
- Accession Number
- AD0405848
Entities
People
- G. F. Langdon