THE EFFECT OF DIFFERENT OPTIONS OF BLADES MAIN ROTOR ON THE X-SHAPED TAIL ROTOR OF THE MI-171 LL
https://doi.org/10.26467/2079-0619-2018-21-1-114-123
Abstract
This paper describes the effect of different rotor blades on the X-shaped tail rotor of the Mi-171 LL, observed conducting flight tests. The tests were carried out on the same helicopter in the similar atmospheric conditions.
The objective of the tests was the comparison of flight performance of two sets of rotor blades of the helicopter Mi-171 LL. However, materials test revealed a difference in the angles of the tail rotor at different MRs with the same takeoff weight.
The authors are grateful to I.G. Peskov, S.R. Zamula and A.I. Orlov for assistance in carrying out this work and the preparation of this article.
Noted that the helicopter takeoff weight when hovering out of ground effect in ISA with blades from polymer composite materials (PCM) exceeds the takeoff weight of the helicopter with the serial blades in the nominal mode of the engine operation at ~ 750kg, in the takeoff mode at ~ 700kg.
Knowing the altitude and climatic characteristics of the engine, the obtained dependence allows to determine the balancing value of jрв on hovering at different combinations of pressure altitude and outside air temperature for a given speed of the main rotor (MR).
It follows from the work that when the same value Nпр(95/nнвпр)3 or Nfact the balancing values of jрв for the helicopter with the main rotor blades from the PCM is less than for the helicopters with serial blades by 0.5…0.9°. The difference in the angles of the tail rotor increases with growing of Nепр(95/nнвпр)3 (Nfact). Perhaps this is caused by different induction effect of the main rotor on the tail rotor to the MR from PCM and the serial ones.
As follows from the materials, the thrust of the main rotor with blades from PCM with the same engine power is more in comparison with the serial blades. Consequently inductive speeds of the main rotor are more and the angles of the tail rotor are less. It can be assumed that a large induced velocity of the main rotor increases the thrust of X-shaped tail rotor.
Supporting agencies: I.G. Piskov, S.R. Zamula, A.I. Orlov
About the Authors
V. A. Ivchin
JSC "Mil Moscow Helicopter Plant"
Russian Federation
Russian Federation
Valery A. Ivchin -Candidate of Technical Sciences, Head of the Department of Aerodynamics and Dynamics of Helicopters JSC «Mil Moscow Helicopter Plant».
Tomilino, Moscow region
V. A. Nikiforov
JSC "Mil Moscow Helicopter Plant"
Russian Federation
Russian Federation
Vladimir A. Nikiforov - Lead Designer JSC «Mil Moscow Helicopter Plant».
Tomilino, Moscow region
K. Yu. Samsonov
Moscow Aviation Institute
Russian Federation
Russian Federation
Konstantin Yu. Samsonov -Graduate Student Moscow Aviation Institute.
Moscow
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Review
For citations:
Ivchin V.A., Nikiforov V.A., Samsonov K.Yu. THE EFFECT OF DIFFERENT OPTIONS OF BLADES MAIN ROTOR ON THE X-SHAPED TAIL ROTOR OF THE MI-171 LL. Civil Aviation High Technologies. 2018;21(1):114-123. (In Russ.) https://doi.org/10.26467/2079-0619-2018-21-1-114-123
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