**Notations**


*Discrete Vortex Cylinders Method for Calculating the Helicopter Rotor-Induced Velocity DOI: http://dx.doi.org/10.5772/intechopen.93186*


*dξ*

*ds* <sup>¼</sup> cos *<sup>τ</sup>*, *<sup>d</sup><sup>ζ</sup>*

3.The results showed, repeating the results of the classical impulse rotor theory on hover mode in the plane of the rotor and in the wake far behind the rotor.

4.We showed the capabilities of the method in calculating the distribution of inductive speeds in the plane of the rotor and the space outside it, also in calculating the bevel of the flow in the stabilizer and tail rotor regions.

5.We confirmed the fine capabilities of the developed method in calculating

To study the effectiveness of the method of discrete vortex cylinder embedded in the helicopter trimming computer program. The calculations are performed with the original data of the helicopter "ANSAT." The program allows calculating the trimming characteristics of helicopter rotor: aerodynamic performance, the loading

The method of discrete vortex cylinders is successfully used for calculating inductive velocities in the aeroelasticity blade model for ANSAT helicopter main

1.Modeling of the earth effect using the method of vortices reflected from the

2.Construct a discrete model of the fuselage using the CFD-method to study the

3.Refinement of the discrete cylinders method for calculating the vortex ring

4.Extension of the discrete vortex cylinder method to the nonlinear Shaidakov's

5.Application of the discrete vortex cylinder method to solving helicopter take-

6. Simulation of vortex formation when landing on a snow-covered and dusty

7.Simulation of helicopter dynamics with rotor blades dynamics using the

to Russian educational institutions" (Agreement No. 11.G34.31.0038).

*A x*ð Þ 1, 0, *z*<sup>1</sup> induced-velocity calculated point *aij* element of influence matrix

This work was partially supported by the grant in accordance with the Decree of the Government of the Russian Federation No. 220 "on attracting leading scientists

effect of main rotor blowing with the tail rotor-induced velocity.

regime by the limiting of the vortex cylinder height.

inductive speeds at the low-speed horizontal flight mode.

rotor loads calculation (for example, see [7]).

*Vortex Dynamics Theories and Applications*

of the blades.

**6. Future work**

earth's surface.

vortex theory.

surface.

**Notes**

**Notations**

**116**

off and landing problems.

discrete vortex cylinders method.

*Vortex Dynamics Theories and Applications*
