Time-accurate simulation of flow past PZL W-3A "Sokół" (Falcon) helicopter main rotor in forward flight

• Autorzy: Szulc O. , Doerffer P. , Żółtak J. , Małecki J.
• Języki publikacji: EN

Abstrakty

EN

The paper presents the results of numerical simulations based on the URANS approach and the chimera overlapping grids technique of the main PZL W-3A "Sokół" (Falcon) helicopter rotor in forward flight conditions. The low-speed flight case models the helicopter rotor as parallel to the ground keeping forward speed of approximately 99km/h. Strong Blade-Vortex Interaction (BVI) is responsible for a high level of vibration and noise. The high-speed (266km/h) case reveals two main problems of modern helicopters: compressibility effects due to strong shock-wave boundary layer interaction on the advancing side and separation leading to a dynamic stall on the retreating side of the rotor. An attempt is made to correlate the results of the simulations with the very limited flight test data.

Słowa kluczowe

EN

helicopter rotor; forward flight; chimera overlapping grid

• Wydawca: Politechnika Gdańska
• Czasopismo: TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
• Rocznik: 2013
• Tom: Vol.17, No 1-2
• Strony: 43--61
• Opis fizyczny: Bibliogr. 6 poz., rys., tab.

Twórcy

autor

Szulc O.

• Institute of Fluid-Flow Machinery

autor

Doerffer P.

• Institute of Fluid-Flow Machinery

autor

Żółtak J.

• Institute of Aviation

autor

Małecki J.

• PZL-Świdnik S. A.

Bibliografia

• [1] Kania W and Stalewski W 2000 Proc. 22nd Congress of the Int. Council of the Aeronautical Sciences, Harrogate, United Kingdom, pp. 181.1 -181.10
• [2] Doerffer P and Szulc O 2010 Aero-acoustical Analysis of Two Main Rotors of the Helicopter. 4-bladed Rotor Based on the NACA Profiles. Geometrical Model. Grid Generation and Test Simulations. IMP PAN Internal Report No. 245 (in Polish)
• [3] Doerffer P and Szulc O 2011 Aero-acoustical Analysis of Two Mam Rotors of the Helicopter. 4-bladed Rotor Based on the NACA Profiles. Numerical Simulation of the Rotor in Low- and High-speed Forward Flight. IMP PAN Internal Report No. 18 (in Polish)
• [4] Kroll N, Rossow C. Schwamborn D. Becker K and Heller G 2002 Proc. 23rd Congress of the Int. Council of the Aeronautical Sciences, Toronto, Canada, pp. 105.1-105.20
• [5] Schwarz T 2005 Proc. 31st European Rotorcraft Forum. Florence, Italy, pp. 689-706
• [6] Rung T. Lübcke H. Franke M. Xue L. Thiele F and Fu S 1999 Proc. 4th Int. Symposium on Engineering Turbulence Modelling and Measurements, Ajaccio, France, pp. 659-668