Accession Number:

AD0759534

Title:

Summary of Design Studies and Results of Model Tests of the Folding-Proprotor Aircraft Concept

Descriptive Note:

Final rept

Corporate Author:

BELL HELICOPTER TEXTRON INC FORT WORTH TX

Personal Author(s):

Report Date:

1972-07-01

Pagination or Media Count:

226.0

Abstract:

Design studies and wind-tunnel test investigations were conducted to define preliminary designs of folding-proprotor VTOL aircraft for USAF rescue and transport missions and to identify and investigate technical risk areas. The aircraft had gross weights of 66,000 pounds and extended hover capability to 7000 feet. Convertible fan-jet engines provided forward flight speeds to 452 knots with blades folded. Technical risk areas associated with the aircraft designs were found to be in areas of mechanisms, aerodynamics, stability and control, and dynamics. A dynamic wind-tunnel investigation, conducted with a semispan aeroelastic model, demonstrated successful continuous stopfoldunfold start sequences, and freedom from proprotorpylon stability and blade flutter.

Subject Categories:

  • Helicopters
  • VSTOL

Distribution Statement:

APPROVED FOR PUBLIC RELEASE