Aerodynamic design of tsagi helicopter airfoils

Aeronautical and Space-Rocket Engineering

Aerodynamics and heat-exchange processes in flying vehicles


Animitsa V. A.*, Golovkin V. A.*, Nikol'skii A. A.*

Central Aerohydrodynamic Institute named after N.E. Zhukovsky, TsAGI, 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia



The article discusses the distinctive features of helicopter airfoils flow-around generating integral criteria of their aerodynamic perfection. It demonstrates the importance of the concept of helicopter aerodynamic airfoils and its role in the system, including all cycles of aerodynamic configuration development of rotor blades from the objective function definition up to the elaboration (based on calculation and experimental studies) of recommendations for industrial application. The authors suggest a new approach to comparing experimental helicopter airfoils performance by to the three integral criteria.

The article describes a systematic approach to the development of TsAGI helicopter airfoils for aerodynamic configuration of rotor blades based on the calculation and experimental system. This system empooys the qualitative relationship between the objective vector of main rotor aerodynamic performance and the set of objective vectors of airfoil aerodynamic performance, which allows developing prospective helicopter airfoils for main and tail rotor blades for multipurpose helicopter based on the aerodynamic design procedure. The features of the complex procedure of aerodynamic design of helicopter airfoils used in TsAGI, and its main structural elements are under discussion. Quantitative relationship establishing of the main rotor performance vector and the airfoils performance vectors is performed at the stage of experimental studies of new aerodynamic configurations on large-scale models of the main rotor in wind tunnels. Some results of such

kind of studies are presented on the example of comparing conventional and perspective rotor configurations.

Experiments in the wind tunnel and flight tests confirm the effectiveness of the application and the need to further developing the new series of TsAGI airfoils designed to create aerodynamic configurations of the main rotor blades of modified and prospective helicopters with improved aerodynamic performance.

Based on the TsAGI calculation and experimental system, the article suggests new aerodynamic airfoil configurations of modified and perspective main and tail rotors of domestic helicopters. In particular, the TsAGI developments and their implementation in the design of the blades of the experimental main rotor at Mil Moscow Helicopter Plant allowed reaching record flight speeds of the helicopter — the flying laboratory of the classic single-rotor scheme (without wing and additional propulsive devices).


TsAGI helicopter airfoil, aerodynamic airfoil design, main rotor blade


  1. Golovkin M.A., Efremov A.A., Leont’ev V.A. Ocherki po istorii razvitiya issledovaniya TsAGI po vertoletam i shtoporu samoletov (Essays on history of the development of TSAGI research on helicopters and aircraft nose-spin), Moscow, TsAGI, 2017, pp. 84-85.

  2. Baskin V.E., Vil’dgrube L.S., Vozhdaev E.S., Maikapar G.I. Teoriya nesushchego vinta (Main rotor theory), Moscow, Mashinostroenie, 1973, 363 p.

  3. Bousman W. Airfoil Design and Rotorcraft Performance. Proceedings of the 58th Annual Forum of the American Helicopter Society (Montreal, Canada, 11-13 June 2002).

  4. Golovkin V.A., Kalyavkin V.M. Trudy TsAGI, issue 1685, Moscow, Izdatel’skii otdel TsAGI, 1975, pp. 3-19.

  5. Ignatkin Yu.M., Makeev P.V., Grevtsov B.S., Shomov A.I. A nonlinear blade vortex propeller theory and its applications to estimate aerodynamic characteristics for helicopter main rotor and anti-torque rotor. Aerospace MAI Journal, 2009, vol. 16, no. 5, pp. 24-31.

  6. Ignatkin Yu.M., Makeev P.V., Shomov A.I. Trudy MAI, 2010, no. 38. URL:

  7. Leont’ev V.A. Uchenye zapiski TsAGI, 2010, vol. XLI, no. 5, pp. 67-80.

  8. Nikol’skii A.A. Uchenye zapiski TsAGI, 2014, vol. XLV, no. 3, pp. 20-29.

  9. Nikol’skii A.A. Trudy MAI, 2016, no. 88. URL:

  10. Nikol’skii A.A Universal geometric transformation method PGT for aircraft design. 44th European rotorcraft forum, 2018, vol. 1, no. 40, pp. 456-467.

  11. Animitsa V.A., Golovkin V.A., Nikol’skii A.A. Patent RU 2547475 C1, 10.04.2015.

  12. Animitsa V.A., Golovkin V.A., Nikol’skii A.A. Patent RU 2559181 C1, 10.08.2015.

  13. Animitsa V.A., Golovkin V.A., Nikol’skii A.A. Patent RU 2558539 C1, 10.08.2015.

  14. Dadone L.U. Advanced airfoils for helicopters rotor appplication. UK Patent Application GB 2059373A, 28.09.1979.

  15. Noonan K.W. Family of airfoil shapes for rotating blades. US Patent 4412664, 01.11.1983.

  16. Noonan K.W. High lift, low pitching moment airfoils. US Patent 4776531, 11.10.1988.

  17. Reneaux J., Bezard H., Thibert J.J. Etudes de profilspour helicopter. La Recherche Aérospatiale, 1995, no. 3, pp. 151-166.

  18. Horstmann K.H., Köster H., Polz G. Improvement of two blade sections for helicopter rotors. 10th European Rotorcraft Forum (28-31 August 1984, Hague, Netherlands). Paper No 1. URL:

  19. Polz G., Schimke D. New aerodynamic rotor blade design at MBB. 13th European Rotorcraft Forum (8-11 September 1987, Ar1es, France). Paper No 2.19, 1987. URL:

  20. Nakadate M., Obukata M. Design of New Generation Rotor Blade Airfoils Using Navies-Stokes. 20th European Rotorcraft Forum (4-7 October 1994, Amsterdam, Netherlands). Paper No. 33, 1994.

  21. INTERFAX, 2016. URL: — informational site of MAI

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