EVALUATION OF HIGH-TEMPERATURE CAST-IN-PLACE TRANSPARENT PLASTIC LAMINATES SUITABLE FOR CANOPIES ON SUPERSONIC FIGHTER AIRCRAFT

Abstract

Wind tunnel tests conducted at Mach 2.75 conditions on as cast Plex 55 indicated that no rippling or flow of the surface will occur in a high-speed air stream. Flexural and tensile properties were obtained for the epoxy thermal barrier material. Operational temperature cycle testing at Test C conditions was continued. Several premature specimen failures were experienced, but the test specimen configuration was redesigned to eliminate this tendency to failure, and new test specimens are now ready for testing. No forming or laminating attempts were made during this period on either the canopy or windshield side panel. The no. 1 side panel casting indicated that a different type of forming mold would be required for this port on of the program. The new mold has been fabricated and is nearly ready for use. (Author)

Document Details

Document Type
Technical Report
Publication Date
Feb 08, 1961
Accession Number
AD0265655

Entities

Organizations

  • Goodyear Aerospace

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Composite Materials
  • Fighter Aircraft
  • High Temperature
  • Laminated Plastics
  • Laminates
  • Materials
  • Supersonic Aircraft
  • Tensile Properties
  • Test And Evaluation
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Materials science

Readers

  • Aerospace Test and Evaluation
  • Metallurgy
  • Polymer Science and Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow