Effects of Large-Droplet Ice Accretion on Airfoil and Wing Aerodynamics and Control

Details

• Creators:
  Bragg, M. B. ; Loth, E.
• Corporate Creators:
  University of Illinois at Urbana-Champaign
• Corporate Contributors:
  United States. Department of Transportation. Federal Aviation Administration. Office of Aviation Research ; United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
• Subject/TRT Terms:
  • Aerodynamics
  • Flow
  • Icing
  • Boundary layer
  • Airfoils
  • Airplanes
  • Ice prevention
  • Leading edges
• Publication/ Report Number:
  DOT/FAA/AR-00/14
• Resource Type:
  Tech Report
• Geographical Coverage:
  United States
• Edition:
  Final Report
• Contracting Officer:
  Riley, James
• Corporate Publisher:
  United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
• Description:
  An integrated experimental and computational investigation was conducted to determine the effect of simulated ridge ice shapes on airfoil aerodynamics. These upper-surface shapes are representative of those which may form aft of protected surfaces in super-cooled large droplet conditions. The simulated ice shapes were experimentally tested on a modified NACA 23012 (23012m) airfoil and NLF 0414 airfoil at Reynolds numbers of 1.8 million for a range of protuberance locations, sizes, and shapes. The computational study investigated the cases encompassed by the experimental study but in addition included higher Reynolds numbers and other airfoils from the NASA Commuter Airfoil Program.
• Format:
  PDF
• Download URL:
  https://rosap.ntl.bts.gov/view/dot/93872/dot_93872_DS1.pdf
• File Type:
  [PDF - 3.84 MB]
• Collection(s):
  FAA William J. Hughes Technical Center for Advanced Aerospace
• Main Document Checksum:
  urn:sha-512:6fcee3569a139f2e124cf36ac631a36acd8cfe32f9b73fed49c7bbb1dc9e7512ef5dc245beab7d7498cbf29ae53345997853dc88d79065cd692f8697664fefd3