Effect of high lift flap systems on the conceptual design of a 1985 short-haul commercial stol tilt rotor transport

Technical Report · Sat Apr 01 04:00:00 EST 1978

OSTI ID:6761926

Shovlin, M D; Gambucci, B J

The performances of a derivative concept of a 1985 STOL tilt rotor transport, and of a second concept having a complex mechanical flap system similar to a short field B737 aircraft were compared for a 370 kilometer (200 nautical mile) short haul mission. The flap system of the latter allowed lift to be shifted from the rotor system to the wing, permitting a 26% reduction in dynamic component weight, while also permitting the use of a smaller wing. The wing and disc loading of this concept were 5746 (120 psf) and 1915 (40 psf) newtons/m/sup 2/, respectively, while the wing and disc loading of the derivative concept were 4788 (100 psf) and 1197 (25 psf) newtons/m/sup 2/, respectively. The high lift wing tilt rotor showed slightly improved fuel usage over its entire operating range and about 6 to 8% improvement in direct operating costs, resulting from its improved cruise efficiency and reduced weight. Other advantages include improved reliability with potentially reduced maintenance and better riding quality.

• Research Organization: National Aeronautics and Space Administration, Moffett Field, CA (USA). Ames Research Center
• OSTI ID: 6761926
• Report Number(s): N-78-21094; NASA-TM-78474; A-7364
• Country of Publication: United States
• Language: English

Related Subjects

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
320201* -- Energy Conservation
Consumption
& Utilization-- Transportation-- Air & Aerospace
AIRCRAFT
DESIGN
FUEL ECONOMY