THEORETICAL STUDY OF THE EFFECT OF BLADE ICE ACCRETION ON THE POWER-OFF LANDING CAPABILITY OF A WESSEX HELICOPTER

The effect of rotor blade icing on the performance of a Wessex helicopter has been investigated theoretically. The paper concentrates on the behavior of the aircraft following total power failure, but some consideration is also given to the performance losses in forward flight. An attempt is made to relate the torque increases calculated in forward flight to the performance in autorotation and the ability to make a power-off landing is studied. The effect of blade ice is represented by a decrease in lift curve slope and an increase in the drag of the blade section, with the magnitude and spanwise distribution of the changes being varied to cover a range of conditions. The predictions show that the time in which a pilot must react to a total power failure, so as to avoid a drop in rotor speed below the minimum permitted level, can be correlated with the excess torque at the moment of engine failure. No simple relation between the performance losses in the steady autorotative descent could be found because of the different load distribution on the blades.

  • Corporate Authors:

    Pergamon Press, Incorporated

    Maxwell House, Fairview Park
    Elmsford, NY  United States  10523
  • Authors:
    • Young, C
  • Publication Date: 1978

Media Info

  • Features: References;
  • Pagination: p. 11-25
  • Serial:
    • Vertica
    • Volume: 2
    • Issue Number: 1
    • Publisher: Pergamon Press, Incorporated

Subject/Index Terms

Filing Info

  • Accession Number: 00188536
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Files: TRIS
  • Created Date: Feb 27 1979 12:00AM