AERODYNAMIC ANALYSIS OF HELICOPTER ROTOR USING FREE WAKE VORTEX LATTICE METHOD

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HASHEMABADI M.; HEJRANFAR K.

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Journal: Year:2007 | Volume:40 | Issue:6 (100) Page(s): 895-906

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Title

AERODYNAMIC ANALYSIS OF HELICOPTER ROTOR USING FREE WAKE VORTEX LATTICE METHOD

Author(s)

HASHEMABADI M. | HEJRANFAR K. | Issue Writer Certificate

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Abstract

The accurate computation of helicopter rotor flow leads to an accurate calculation of rotor blade aerodynamic loads. The flowfield around a rotor is difficult to model due to the presence of vortical wake. The complexity of the rotor flowfield results from the effects of strong vortical wake and primary vortical structures that are convected away from the rotor disk at relatively low speeds. In the present work, a free wake vortex lattice method is used to accurately predict the vortical wake and blade loading of an isolated rotor in hover. In the vortex lattice method, the blades are modeled as flat plates with zero thickness and ring vortices are distributed on the surface of each blade. When the blades rotate, the vortices are shed into the wake and freely moved with a velocity induced by the effects of the vortices located on the blades and in the wake. The wake can freely deform over time to take its natural shape. The distribution of lift can be computed from the strength of each vortex on the blade. The aerodynamic analysis of a wing in oscillating motion for different reduced frequencies is performed to show the accuracy of the free wake vortex lattice method for unsteady calculations. Then, the aerodynamic calculations are performed for a hovering helicopter rotor for two operating conditions of subsonic and transonic tip Mach numbers (Mtip = 0.44, 0.88). To accurately compute the compressible flow case, the Prandtl- Glauert correction is applied to the Biot-Savart Law. The present calculations based on the free wake vortex lattice method are compared with available theoretical and experimental results. The effects of number of panels, vortex core radius and also computational time step on the aerodynamic results and wake structure are also studied. Finally, the capability of the free wake vortex lattice method for aerodynamic analysis of the rotor blades with twist is demonstrated.

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APA: Copy

HASHEMABADI, M., & HEJRANFAR, K.. (2007). AERODYNAMIC ANALYSIS OF HELICOPTER ROTOR USING FREE WAKE VORTEX LATTICE METHOD. JOURNAL OF FACULTY OF ENGINEERING (UNIVERSITY OF TEHRAN), 40(6 (100)), 895-906. SID. https://sid.ir/paper/14373/en

Vancouver: Copy

HASHEMABADI M., HEJRANFAR K.. AERODYNAMIC ANALYSIS OF HELICOPTER ROTOR USING FREE WAKE VORTEX LATTICE METHOD. JOURNAL OF FACULTY OF ENGINEERING (UNIVERSITY OF TEHRAN)[Internet]. 2007;40(6 (100)):895-906. Available from: https://sid.ir/paper/14373/en

IEEE: Copy

M. HASHEMABADI, and K. HEJRANFAR, “AERODYNAMIC ANALYSIS OF HELICOPTER ROTOR USING FREE WAKE VORTEX LATTICE METHOD,” JOURNAL OF FACULTY OF ENGINEERING (UNIVERSITY OF TEHRAN), vol. 40, no. 6 (100), pp. 895–906, 2007, [Online]. Available: https://sid.ir/paper/14373/en

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