LIGHT WEIGHT BLADE STUDY AND DEVELOPMENT PROGRAM

Abstract

Work efforts from the Phase I summary report on the properties of suitable light weight blade materials, blade construction are reported. It was established that the optimum blade, considering the contractural stipulation of a 13.5 ft.diameter turbo propeller blade for conventional aircraft equipped with engines rated from 3,000 to 4,000 shaft horsepower, CL of .446. The evaluation studies in the material strength, manufacturing feasibility, and fabrication cost areas showed that a fiberglass reinforced plastic blade would fulfill the requirements to the best advantage. From the two above recommendations a complete blade study was performed on five basic materials on the basis of an assumed design condition and structurally optimized with considerations being given to manufacturing limitations and the working allowable stresses of each material. (Author, modified-PL).

Document Details

Document Type
Technical Report
Publication Date
Jul 26, 1962
Accession Number
AD0290596

Entities

People

  • W.j. Jasinski

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Blades
  • Construction
  • Diameters
  • Fabrication
  • Fiberglass
  • Fibers
  • Horsepower
  • Manufacturing
  • Materials
  • Propeller Blades
  • Propellers
  • Test And Evaluation

Readers

  • Aerodynamics.
  • Reinforced Composite Materials
  • Software Engineering