Configuration Design Analysis of a Prop/Rotor Aircraft
Final technical rept. 15 Apr-15 Aug 1969 on phase 1
BOEING VERTOL CO PHILADELPHIA PA
Pagination or Media Count:
Basic design studies on proprotor aircraft are summarized. This program is to determine design criteria and demonstrate the adequacy of technology by designing a full-scale proprotor aircraft and by designing, manufacturing and testing scaled models. Selected from preliminary design and performance sensitivity tradeoffs was a proprotor 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 proprotor 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.
- Transport Aircraft