INFLUENCE OF SWEEP ON THE AERODYNAMIC LOADING OF AN OSCILLATING NACA 0012 AIRFOILS -- VOLUME 1. TECHNICAL REPORT

An investigation was conducted on the effects of sweep on the induced aerodynamics load response of airfoils. Aerodynamic experiments were performed on an oscillating NACA 0012 airfoil in the United Technologies Research Center (UTRC) Main Wind Tunnel utilizing a tunnel-spanning wing in both unswept and 30 degree swept configurations. The airfoil was tested in steady-state and in oscillatory pitch about the quarter chord. The unsteady aerodynamic loading was measured using pressure transducers along the chord. A stability analysis of the data was performed. It was determined that at mean incidence angles greater than 9 degrees, sweep tends to reduce the stability margin. The fluctuating pressures on a steady airfoil in stalled flow were also examined.

  • Corporate Authors:

    National Aeronautics and Space Administration

    600 Independence Avenue, SW
    Washington, DC  USA  20546
  • Authors:
    • St Hilaire, A O
    • Carta, F O
    • Fink, M R
    • Jepson, W D
  • Publication Date: 1979-5

Media Info

  • Features: References;
  • Pagination: 139 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00301382
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Report/Paper Numbers: CR-3092 Contr Rpt.
  • Files: TRIS
  • Created Date: Feb 11 1980 12:00AM