INVESTIGATION OF NONLINEAR AEROELASTIC BEHAVIOR OF AIRFOILS WITH FLOW SEPARATION BASED ON CUBIC STATIC STALL MODELING

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SHAMS SHAHROKH; KAZEMI MOHAMMAD REZA; MIRZAVAND BOROJENI BABAK; KHOJASTEH BAKHTEH KOUPAIE ZAHRA

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Journal: Modares Mechanical Engineering Year:2017 | Volume:16 | Issue:12 Page(s): 311-322

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Title

INVESTIGATION OF NONLINEAR AEROELASTIC BEHAVIOR OF AIRFOILS WITH FLOW SEPARATION BASED ON CUBIC STATIC STALL MODELING

Author(s)

SHAMS SHAHROKH | KAZEMI MOHAMMAD REZA | MIRZAVAND BOROJENI BABAK | KHOJASTEH BAKHTEH KOUPAIE ZAHRA

Keywords

STATIC STALL

WAGNER UNSTEADY AERODYNAMIC

INTEGRATION HISTORICAL METHOD

LIMIT CYCLE OSCILLATIONS (LCO)

Abstract

In this paper, by defining a new paradigm for nonlinear aerodynamic equations of flow separation and STATIC STALL, a new form of nonlinear aeroelastic equations for two degrees of freedom airfoils (torsional and bending) are presented. Structural equations are based on the nonlinear mass-spring model which includes the nonlinear quadratic and cubic terms. Aerodynamic equations are obtained by combining the unsteady Wagner model and the nonlinear lift coefficient-angle of attack for simulating stall using a cubic approximation. Hamilton’s principle and Lagrange equations were used to derive the aeroelastic equations. The obtained integro-differential nonlinear aeroelastic equations are solved using a timehistory integration method. The aeroelastic behavior of the airfoil is compared in both unsteady and quasi-steady flow. Using the time-history method compared to the phase space method leads to fewer equations. The results show that the aeroelastic behavior of airfoil with a linear structure, using a nonlinear aerodynamic theory for the stall, causes oscillations with a limit cycle in unsteady and quasisteady flow compared to other linear aerodynamic theories. Also, the use of the cubic curve instead of the piecewise linear curves which are commonly used in other references, causes an apparent complication of the equations, reduces the computational time due to faster convergence in solution and makes the reduction in errors. The results show that the use of nonlinear aerodynamic STATIC STALL not only reduces the instability velocity, but also reduces the amplitude of limit cycle oscillations in both unsteady and quasi-steady regimes.

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APA: Copy

SHAMS, SHAHROKH, KAZEMI, MOHAMMAD REZA, MIRZAVAND BOROJENI, BABAK, & KHOJASTEH BAKHTEH KOUPAIE, ZAHRA. (2017). INVESTIGATION OF NONLINEAR AEROELASTIC BEHAVIOR OF AIRFOILS WITH FLOW SEPARATION BASED ON CUBIC STATIC STALL MODELING. MODARES MECHANICAL ENGINEERING, 16(12 ), 311-322. SID. https://sid.ir/paper/706514/en

Vancouver: Copy

SHAMS SHAHROKH, KAZEMI MOHAMMAD REZA, MIRZAVAND BOROJENI BABAK, KHOJASTEH BAKHTEH KOUPAIE ZAHRA. INVESTIGATION OF NONLINEAR AEROELASTIC BEHAVIOR OF AIRFOILS WITH FLOW SEPARATION BASED ON CUBIC STATIC STALL MODELING. MODARES MECHANICAL ENGINEERING[Internet]. 2017;16(12 ):311-322. Available from: https://sid.ir/paper/706514/en

IEEE: Copy

SHAHROKH SHAMS, MOHAMMAD REZA KAZEMI, BABAK MIRZAVAND BOROJENI, and ZAHRA KHOJASTEH BAKHTEH KOUPAIE, “INVESTIGATION OF NONLINEAR AEROELASTIC BEHAVIOR OF AIRFOILS WITH FLOW SEPARATION BASED ON CUBIC STATIC STALL MODELING,” MODARES MECHANICAL ENGINEERING, vol. 16, no. 12 , pp. 311–322, 2017, [Online]. Available: https://sid.ir/paper/706514/en

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