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COMPUTATIONAL STUDY OF FLOW PARAMETERS IN THE REGION OF THE TAIL ROTOR LOCATION AT LOW SPEEDS OF SLIDING FLIGHT

Volume 45, Issue 8, 2014, pp. 957-975
DOI: 10.1615/TsAGISciJ.2015013619
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ABSTRACT

The present paper considers the calculation method of vortex wakes and instantaneous induced velocities for main and tail rotors in disk planes for each rotor, taking into account their mutual influence. The study is based on the nonlinear vortex theory, without diffusion of vortex wakes, but taking into account the vortex finite thickness. The wake shape behind the tail rotor, the instantaneous induced velocities of the main and tail rotor disks, and the tail rotor aerodynamic characteristics in flight mode μ = 0.0917 (V = 20 m/s) with sliding angles −90° ≤ β ≤ 90° are defined and are shown in the form of plots.

CITED BY
  1. Ivchin V. A., Samsonov K. Y., Kasimov A. M., Popov A. I., Development of the technical solution to prevent a single-rotor helicopter from entering uncontrolled rotation, Civil Aviation High Technologies, 25, 3, 2022. Crossref

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