Skin Friction Drag Due to Nuclear Damage

Abstract

Typical thin aircraft skin samples were fabricated of aluminum and fiberglass and painted with black enamel and other coatings. The samples were exposed to fluence levels from 20 to 200 cals/sq cm to produce simulated nuclear thermal damage. Their skin friction was then measured at Mach numbers of 0.5 and 0.8 and Reynolds' numbers of 6 to 16 million. An equivalent sand roughness was calculated from the drag. Results showed an initial increase in roughness which then remained constant until the skin melted, debonded or suffered other severe damage.

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Document Details

Document Type
Technical Report
Publication Date
Sep 30, 1977
Accession Number
ADA061444

Entities

People

  • E. York
  • W. Fleener

Organizations

  • Boeing

Tags

Communities of Interest

  • Air Platforms
  • Counter WMD
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • High Temperature
  • Honeycomb Cores
  • Honeycomb Structures
  • Mach Number
  • Materials
  • Materials Laboratories
  • Measurement
  • Military Aircraft
  • Plastic Explosives
  • Roughness
  • Skin Friction
  • Test Equipment
  • Test Methods
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Structural Health Monitoring of Composite Structures.
  • Surface Engineering/Surface Coating Technology.