Accession Number:

AD0489862

Title:

SUPPLEMENTARY STUDY REPORT ROTOR/WING CONCEPT STUDY

Descriptive Note:

Corporate Author:

HUGHES TOOL CO CULVER CITY CA AIRCRAFT DIV

Personal Author(s):

Report Date:

1966-02-01

Pagination or Media Count:

35.0

Abstract:

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.

Subject Categories:

  • Helicopters
  • VSTOL
  • Hydraulic and Pneumatic Equipment

Distribution Statement:

APPROVED FOR PUBLIC RELEASE