XH-59A ABC Technology Demonstrator Altitude Expansion and Operational Tests
Abstract
this report presents the results of two flight test programs conducted with the XH-59A Advancing Blade Concept demonstrator aircraft. The first program, conducted in the auxiliary propulsion configuration, consisted of altitude and center-of-gravity envelope expansion testing. Test results verified the concept of developing lift primarily on the advancing rotor blades to dramatically improve lift and speed potential. The XH-59A achieved a maximum speed of 263 knots true airspeed and demonstrated a service ceiling of 25,500 feet. The entire flight envelope was demonstrated without classical retreating blade stall. Rotor loads and stresses and rotor tip clearance followed predicted trends and were controllable. Limited center-of-gravity envelope expansion was accomplished. The second program consisted of operational tests conducted primarily in the nap-of-the-earth and contour flight environments, using both the auxiliary and helicopter propulsion modes. The compact ABC design and smaller rotor diameter enhanced operation in confined areas. Operational test results showed the ABC to be a viable alternative concept for future tactical aircraft.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1981
- Accession Number
- ADA111114
Entities
People
- A. J. Ruddell
Organizations
- United Technologies Corporation