Hostname: page-component-cd9895bd7-jkksz Total loading time: 0 Render date: 2024-12-23T14:54:50.865Z Has data issue: false hasContentIssue false
  • English
  • Français

Nonlinear Aerodynamic Effects on Transonic Flap Buzz, Tail Flutter and Limit-Cycle Oscillations of Two-Dimensional Wing-Flap-Tail Configurations

Published online by Cambridge University Press:  05 May 2011

J.-C. Cheng
J.-C. Cheng*
Affiliation:
Department of Aeronautical Engineering, National Formosa University, Yuenlin, Taiwan 63208, R.O.C.
*
*Assistant Professor
Get access

Abstract

The transonic tail flutter and flap buzz under the wing-flap-tail configurations are analyzed utilizing a dynamic grid capability of unstructured Euler solver coupled with an appropriate aeroelastic solver. From the results, the presence of a forewing, either stationary or oscillating, has significant effect on the tail flutter characteristics. In particular, the tail motion may be in resonance with the oscillating wing before the onset of flutter, which is dangerous to the tail structure because of the large amplitude oscillations. Besides, a complicated aerodynamic and aeroelastic interference of the tail have been found due to the unsteady disturbance which is a strong variability of flow structure induced by the buzz of the flap. In the high transonic flow regime, the flap buzz with limit-cycle oscillations does occur, and the influence induced by the tail is not important. The increasing restoring force at the pivot where the flap joints with the wing will reduce the flap oscillations that improves the effect of the flap buzz.

Keywords

Transonic buzzFlutterLimit-cycle oscillationWing-flap-tailUnstructured dynamic grid solver.
Type
Articles
Information
Journal of Mechanics , Volume 25 , Issue 4 , December 2009 , pp. 451 - 463
Copyright
Copyright © The Society of Theoretical and Applied Mechanics, R.O.C. 2009

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

1.Shankar, V. and Malmuth, N. D., “Transonic Flow Calculations over Two-Dimensional Canard-Wing System,” Journal of Aircraft, 18, pp. 108–114 (1981).CrossRefGoogle Scholar
2.Batina, J. T., “Unsteady Transonic Flow Calculations for Two-Dimensional Canard-Wing Configurations,” Journal of Aircraft, 23, pp. 190–198 (1986).Google Scholar
3.Rausch, R. D., Batina, J. T. and Yang, T. Y., “Euler Flutter Analysis of Airfoils Using Unstructured Dynamic Meshes,” Journal of Aircraft, 27, pp. 436–443 (1990).CrossRefGoogle Scholar
4.Batina, J. T., “Unsteady Euler Algorithm with Unstructured Dynamic Meshes for Complex-Aircraft Aerodynamic Analysis,” AIAA Journal, 29, pp. 327–333 (1991).CrossRefGoogle Scholar
5.Yang, S. Y. and Chen, K. H., “Numerical Study of Turbulent Flows over Vibrating Blades with Positive Interblade Phase Angle,” Journal of Mechanics, 23, pp. 149–157 (2007).CrossRefGoogle Scholar
6.Pan, D. and Cheng, J. C., “Unstructured Euler Flutter Analysis of Two-Dimensional Wing-Tail Configuration,” Journal of Aircraft, 32, pp. 1152–1155 (1995).CrossRefGoogle Scholar
7.Chen, X., Zha, G. C. and Yang, M. T., “Numerical Simulation of 3-D Wing Flutter with Fully Coupled Fluid-Structural Interaction,” Computers and Fluids, 36, pp. 856–867 (2007).CrossRefGoogle Scholar
8.Thomas, J. P., Dowell, E. H. and Hall, K. C., “Nonlinear Inviscid Aerodynamic Effects on Transonic Divergence, Flutter, and Limit-Cycle Oscillations,” AIAA Journal, 40, pp. 638–646 (2002).CrossRefGoogle Scholar
9.Kholodar, D. B., “Limit-Cycle Oscillations of a Typical Airfoil in Transonic Flow,” Journal of Aircraft, 41, pp. 1067–1072 (2004).CrossRefGoogle Scholar
10.Zhang, Z., Yang, S. and Liu, F., “Prediction of Flutter and LCO by an Euler Method on Non-Moving Cartesian Grids with Boundary-Layer Corrections,” 43rd AIAA Aerospace Sciences Meeting and Exhibit; Reno, NV, USA, pp. 10–13 (2005).Google Scholar
11.Dietz, G., Schewe, G., Kießling, F. and Sinapius, M., “Limit-Cycle-Oscillation Experiments at a Transport Aircraft Wing Model,” Proceedings of the International Forum on Aeroelasticity and structural Dynamics IFASD, Amsterdam, The Netherlands (2003).Google Scholar
12.Pan, D. and Cheng, J. C., “A Second-Order Upwind Finite-Volume Method for the Euler Solution on Unstructured Triangular Meshes,” International Journal for Numerical Methods in Fluids, 16, pp. 1079–1098 (1993).CrossRefGoogle Scholar
13.Pan, D. and Cheng, J. C., “Upwind Finite-Volume Navier- Stokes Computations on Unstructured Triangular Meshes,” AIAA Journal, 31, pp. 1618–1625 (1993).CrossRefGoogle Scholar
14.Cheng, J. C., “A Two Dimensional Unstructured Euler/Navier-Stokes Solver and its Application to the Flutter Analysis of Wing-Tail Configurations,” Ph.D. Thesis, Institute of Aeronautics and Astronautics, National Cheng Kung University, Taiwan, R.O.C. (1993).Google Scholar
15.Vinokur, M., “An Analysis of Finite-Difference and Finite-Volume Formulations of Conservation Laws,” NACA CR-177416 (1986).Google Scholar
16.Landon, R. H., “NACA 0012 Oscillating and Transient Pitching,” Data Set 3 in AGARD-R-702, Compendium of Unsteady Aerodynamic Measurements (1982).Google Scholar
17.Edwards, J. W., Bennett, R. M. and Whitlow, W. Jr., “Time Marching Transonic Flutter Solutions Including Angle-of-Attack Effects,” Journal of Aircraft, 20, pp. 899–906 (1983).CrossRefGoogle Scholar
18.Isogai, K., “Numerical Steady of Transonic Flutter of a Two-Dimensional Airfoil,” National Aerospace Laboratory, Tokyo, Japan. TR-617T (1980).Google Scholar
19.Bennert, R. M. and Desmarais, R. N., “Curve Fitting of Aeroelastic Transonic Response Data with Exponential Functions, in Flutter Testing Techniques,” NASA SP-415, pp. 43–58 (1975).Google Scholar