정지 비행시 로터 후류 모형 비교 검토Comparison of the Rotor Wake Modeling in Hovering Motion

Cited 0 time in webofscience Cited 0 time in scopus
  • Hit : 253
  • Download : 0
The time marching See wake model of the helicopter rotor in hovering motion is compared with the prescribed wake model. The knows are assumed to three-dimensional unsteady potential flow. In prescribed wake method, an empirical formula firm experimental results is used to calculate the wake geometry until the computed thrust coefficient is well agreed with the given thrust value. However, in free wake method the wake shed from the trailing edge of the rotor blade makes the global wake geometry without any particular restriction. For the case of the single blade rotor in hover, the thrust and lift distribution along the span are obtained and the radial and axial wake geometries, that is, the inner vortex sheets and the tip vortex line are calculated. The numerical results are in good agreement with the results obtained from the prescribed wake geometry. The computed free wake geometry is also at leasts qualitatively in good agreement with the experimental wake geometry which is represented by three wake region; 3-4 revolutions of well defined tip vortex lines, recirculated and expanded zones offer wakes.
Publisher
한국항공우주학회
Issue Date
1997-01
Language
Korean
Citation

한국항공우주학회지, v.25, no.4, pp.11 - 20

ISSN
1225-1348
URI
http://hdl.handle.net/10203/75818
Appears in Collection
AE-Journal Papers(저널논문)
Files in This Item
There are no files associated with this item.

qr_code

  • mendeley

    citeulike


rss_1.0 rss_2.0 atom_1.0