SUPPLEMENTARY STUDY REPORT ROTOR/WING CONCEPT STUDY
HUGHES TOOL CO CULVER CITY CA AIRCRAFT DIV
Pagination or Media Count:
The basic data and analyses from the RotorWing wind tunnel tests were reported in HTC-AD 65-15 AD-473 862L, 863L, 864L. Supplementary analyses of the data with respect to RotorWing rolling and pitching moments in the low- rpm range, RotorWing shaft bending moments in 1-g running-rotor flight, horizontal tail efficiency, and RotorWing blade root bending moments are included in this report.
- Hydraulic and Pneumatic Equipment