Numerical solution of unsteady flow on airfoils with vibrating local flexible membrane

Authors

1 Assistant Professor, Aerospace complex, Malek-Ashtar University of Technology, Tehran, Iran

2 Ph.D. Candidate, Aerospace complex, Malek-Ashtar University of Technology, Tehran, Iran

Abstract

  Unsteady flow separation on the airfoils with local flexible membrane (LFM) has been investigated in transient and laminar flows by the finite volume element method. A unique feature of the present method compared with the common computational fluid dynamic softwares, especially ANSYS CFX, is the modification using the physical influence scheme in convection fluxes at cell surfaces. In contrary to the common softwares which use mathematical methods for discretization, this method considers the physical effects on approximation and discretization and thus increases the accuracy of solution and decreases the diffusion errors significantly. We have focused on the effects of deformation of the membrane on aerodynamic characteristics. For this purpose, first, we have solved the flow on NACA0012 airfoil in Reynolds number of 5000 and investigated the effects of local flexible membrane on aerodynamic coefficients in laminar flow. Then, we have solved the flow over LH37 airfoil in Reynolds number of 1.1×106 and studied the effects of flexible membrane on aerodynamic characteristics in transient flow. To calculate the Reynolds stress in turbulence equations, transient γ-Reθ model has been used. According to the results, airfoil with local flexible membrane prevents flow separation, eliminates laminar separation bubble (LSB) and delays the stall.  

Highlights

  • The Physical Influence Scheme (PIS) is used for approximation of convection fluxes.
  • LFM is found prevent separation and increase the lift coefficient (Laminar Flows).
  • The membrane reduces CD, increases CL and delays the stall angle.

Keywords

Main Subjects

References

[1] O.S. Gabor, A. Koreanschi, R.M. Botez, Low-speed aerodynamic characteristics improvement of ATR 42 airfoil using a morphing wing approach, in:  IECON 2012-38th Annual Conference on IEEE Industrial Electronics Society, IEEE, 2012, pp. 5451-5456.
[2] H. Hasegawa, S. Kumagai, Adaptive separation control system using vortex generator jets for time-varying flow, Journal of applied fluid mechanics, 1 (2008) 9-16.
[3] W. Chuijie, X. Yanqiong, W. Jiezhi, “Fluid roller bearing” effect and flow control, Acta Mechanica Sinica, 19 (2003) 476-484.
[4] O.M. Curet, A. Carrere, R. Waldman, K.S. Breuer, Aerodynamic characterization of wing membrane with adaptive compliance, in:  54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2013, pp. 1909.
[5] Y. Lian, W. Shyy, Three-dimensional fluid-structure interactions of a membrane wing for micro air vehicle applications, AIAA Paper, 1726 (2003) 2003.
[6] Y. Lian, W. Shyy, D. Viieru, B. Zhang, Membrane wing aerodynamics for micro air vehicles, Progress in Aerospace Sciences, 39 (2003) 425-465.
[7] R.E. Gordnier, High fidelity computational simulation of a membrane wing airfoil, Journal of Fluids and Structures, 25 (2009) 897-917.
[8] R. Albertani, B. Stanford, J.P. Hubner, P.G. Ifju, Aerodynamic coefficients and deformation measurements on flexible micro air vehicle wings, Experimental Mechanics, 47 (2007) 625-635.
[9] M. Radmanesh, O. Nematollahi, M. Nili-Ahmadabadi, M. Hassanalian, A novel strategy for designing and manufacturing a fixed wing MAV for the purpose of increasing maneuverability and stability in longitudinal axis, Journal of Applied Fluid Mechanics, 7 (2014) 435-446.
[10] P. Rojratsirikul, Z. Wang, I. Gursul, Unsteady fluid–structure interactions of membrane airfoils at low Reynolds numbers, Experiments in Fluids, 46 (2009) 859-872.
[11] W. Shyy, F. Klevebring, M. Nilsson, J. Sloan, B. Carroll, C. Fuentes, Rigid and flexible low Reynolds number airfoils, Journal of Aircraft, 36 (1999) 523-529.
[12] K.B. Lee, J.H. Kim, C. Kim, Aerodynamic effects of structural flexibility in two-dimensional insect flapping flight, Journal of aircraft, 48 (2011) 894-909.
[13] A. Saboonchi, S. Hassanpour, Heat transfer analysis of hot-rolled coils in multi-stack storing, Journal of materials processing technology, 182 (2007) 101-106.
[14] N.J. Pern, J.D. Jacob, Wake vortex mitigation using adaptive airfoils - The piezoelectric arc airfoil, in:  AIAA, Aerospace Sciences Meeting and Exhibit, 37 th, Reno, NV, 1999.
[15] S.K. Chimakurthi, J. Tang, R. Palacios, C.E. S. Cesnik, W. Shyy, Computational aeroelasticity framework for analyzing flapping wing micro air vehicles, AIAA journal, 47 (2009) 1865-1878.
[16] W. Kang, J.Z. Zhang, P.H. Feng, Aerodynamic analysis of a localized flexible airfoil at low Reynolds numbers, Communications in Computational Physics, 11 (2012) 1300-1310.
[17] R.B. Langtry, J. Gola, F.R. Menter, Predicting 2D airfoil and 3D wind turbine rotor performance using a transition model for general CFD codes, AIAA paper, 395 (2006) 2006.
[18] R.B. Langtry, F.R. Menter, Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes, AIAA journal, 47 (2009) 2894-2906.
[19] C.B. Blumer, E.R. van Driest, Boundary layer transition-freestream turbulence and pressure gradient effects, AIAA Journal, 1 (1963) 1303-1306.
[20] M. Darbandi, M. Taeibi-Rahni, A. Reza Naderi, Firm structure of the separated turbulent shear layer behind modified backward-facing step geometries, International Journal of Numerical Methods for Heat & Fluid Flow, 16 (2006) 803-826.
[21] A. Naderi, M. Darbandi, M. Taeibi‐Rahni, Developing a unified FVE‐ALE approach to solve unsteady fluid flow with moving boundaries, International journal for numerical methods in fluids, 63 (2010) 40-68.
[22] P.F. Lei, J.Z. Zhang, W. Kang, S. Ren, L. Wang, Unsteady flow separation and high performance of airfoil with local flexible structure at low Reynolds number, Communications in Computational Physics, 16 (2014) 699-717.
[23] G. Wichmann, C.H. Rohardt, P. Hirt, Kenndaten für Profile: Profil DLRLH37, in, Luftfahrttechnisches Handbuch – LTH, Band Aerodynamik AD 41102-24, 1998.
[24] D. Schawe, C.H. Rohardt, G. Wichmann, Aerodynamic design assessment of Strato 2C and its potential for unmanned high altitude airborne platforms, Aerospace science and technology, 6 (2002) 43-51.
Journal of Theoretical and Applied Vibration and Acoustics
Volume 2, Issue 1 - Serial Number 1
January 2016
Pages 21-34

Files

Share

How to cite

Statistics