An engineering modification of the blade element momentum equation for vertical descent : an autoration case study

Cuerva Tejero, Alvaro; Sanz Andres, Angel Pedro; Meseguer Ruiz, José y Espino, J.L. (2006). An engineering modification of the blade element momentum equation for vertical descent : an autoration case study. "Journal of The American Helicopter Society", v. 51 (n. 4); pp. 349-354. ISSN 2161-6027. https://doi.org/10.4050/JAHS.51.341.

Descripción

Título: An engineering modification of the blade element momentum equation for vertical descent : an autoration case study
Autor/es:
  • Cuerva Tejero, Alvaro
  • Sanz Andres, Angel Pedro
  • Meseguer Ruiz, José
  • Espino, J.L.
Tipo de Documento: Artículo
Título de Revista/Publicación: Journal of The American Helicopter Society
Fecha: 2006
Volumen: 51
Materias:
Escuela: Instituto de Microgravedad Ignacio Da Riva (UPM)
Departamento: Vehículos Aeroespaciales [hasta 2014]
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

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Resumen

An engineering modification of blade element/momentum theory is applied to describe the vertical autorotation of helicopter rotors. A full non-linear aerodynamic model is considered for the airfoils, taking into account the dependence of lift and drag coefficients on both the angle of attack and the Reynolds number. The proposed model, which has been validated in previous work, has allowed the identification of different autorotation modes, which depend on the descent velocity and the twist of the rotor blades. These modes present different radial distributions of driven and driving blade regions, as well as different radial upwash/downwash patterns. The number of blade sections with zero tangential force, the existence of a downwash region in the rotor disk, the stability of the autorotation state, and the overall rotor autorotation efficiency, are all analyzed in terms of the flight velocity and the characteristics of the rotor. It is shown that, in vertical autorotation, larger blade twist leads to smaller values of descent velocity for a given thrust generated by the rotor in the autorotational state.

Más información

ID de Registro: 40515
Identificador DC: http://oa.upm.es/40515/
Identificador OAI: oai:oa.upm.es:40515
Identificador DOI: 10.4050/JAHS.51.341
Depositado por: Biblioteca ETSI Aeronauticos
Depositado el: 26 May 2016 06:46
Ultima Modificación: 26 May 2016 06:46
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