Aeroelastic Analysis of Engine Nacelle Strake Considering Geometric Nonlinear Behavior

Authors: N. Manoj

Abstract:

The aeroelastic behavior of engine nacelle strake when subjected to unsteady aerodynamic flows is investigated in this paper. Geometric nonlinear characteristics and modal parameters of nacelle strake are studied when it is under dynamic loading condition. Here, an N-S based Finite Volume solver is coupled with Finite Element (FE) based nonlinear structural solver to investigate the nonlinear characteristics of nacelle strake over a range of dynamic pressures at various phases of flight like takeoff, climb, and cruise conditions. The combination of high fidelity models for both aerodynamics and structural dynamics is used to predict the nonlinearities of strake (chine). The methodology adopted for present aeroelastic analysis is partitioned-based time domain coupled CFD and CSD solvers and it is validated by the consideration of experimental and numerical comparison of aeroelastic data for a cropped delta wing model which has a proven record. The present strake geometry is derived from theoretical formulation. The amplitude and frequency obtained from the coupled solver at various dynamic pressures is discussed, which gives a better understanding of its impact on aerodynamic design-sizing of strake.

Keywords: Aeroelasticity, finite volume, geometric nonlinearity, limit cycle oscillations, strake.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1132186

References:

[1] R. E. Gordnier, Computation of limit cycle oscillations of a delta wing, 43rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 22-25 April 2002, Denver, Colorado, USA.
[2] P. J. Attar and R. E. Gordnier. Aeroelastic prediction of the limit cycle oscillations of a cropped delta wing. Journal of Fluids and Structures, 22(1):45 – 58, 2006.
[3] A Arun Kumar, N. Manoj, Amit Kumar Onkar, M Manjuprasad, Fluid-Structure Interaction analysis of a Cropped Delta Wing, 12th International Conference on Vibration Problems, ICOVP 2015, Procedia Engineering 144 (2016) 1205 – 1212, Elsevier journal.
[4] Michael L. and Henderson, R.B.O (1987) ―Nacelle/wing assembly with vortex control device‖. Patent no. US 4685643. Available at: www.google.com/patents/US4685643.pdf.
[5] Raymond E. Gordnier. Computation of limit-cycle oscillations of a delta wing. Journal of Aircraft, 40(6):1206–1208, 2003.
[6] Raymond Gordnier and Reid Melville. Numerical Simulation of Limit-cycle Oscillations of a Cropped Delta Wing Using the Full Navier-Stokes Equations. International Journal of Computational Fluid Dynamics, 14:211–224, 2001.
[7] Jinglong Han Cui Peng. Numerical investigation of the effects of structural geometric and material nonlinearities on limit-cycle oscillation of a cropped delta wing. Journal of Fluids and Structures, 27(4):611 – 622, 2011.
[8] R. E. Gordnier, R. B. Melville, Physical mechanisms for limit-cycle oscillations of a cropped delta wing, 30th AIAA Fluid Dynamics Conference, 28 June - 1 July, 1999, Norfolk, VA.
[9] Ajoy Kumar Kundu, Aircraft design, Cambridge Aerospace series, 2010.