Configuration Design Analysis of a Prop/Rotor Aircraft
Abstract
Basic design studies on prop/rotor aircraft are summarized. This program is to determine design criteria and demonstrate the adequacy of technology by designing a full-scale prop/rotor aircraft and by designing, manufacturing and testing scaled models. Selected from preliminary design and performance sensitivity tradeoffs was a prop/rotor aircraft for a transport mission with a 250 N. mile radius, a cruise speed of 350 knots and a payload of 5 tons with a VTO at 2500 ft and 93F. This aircraft can also perform a rescue mission with a 500 N. mile raidus and a midpoint hover time of 30 minutes. The landing gear was sized for a coverage of 40 and 38 passes when operated on CBR4 soil. A 21% wing thickness is used to provide a wing compatible with high speed drag rise and to satisfy the structural requirements with a minimum weight wing. The prop/rotor utilized has no flap or lag hinges. Rotor blade cyclic pitch is planned to provide both control moments and load alleviation. A hover figure of merit of 75% and a cruise efficiency of 78% are expected for this aircraft. A useful load fraction of 31.6% is projected, based on conservative estimates.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1970
- Accession Number
- AD0869949
Entities
People
- David A. Richardson
- Jaan Liiva
Organizations
- Boeing Rotorcraft Systems