Computational and experimental fluid-structure interaction assessment of a high-lift wing with a slat-cove filler for noise reduction Conference Paper uri icon

abstract

  • 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Airframe noise is a significant component of overall noise produced by transport aircraft during landing and approach (low speed maneuvers). A significant source for this noise is the cove of the leading-edge slat. A slat-cove filler (SCF) has been shown to be effective at mitigating slat noise. The objective of this work is to understand the fluid-structure interaction (FSI) behavior of a superelastic shape memory alloy (SMA) SCF in flow using both computational and physical models of a high-lift wing. Initial understanding of flow around the SMA SCF and wing is obtained using computational fluid dynamics (CFD) analysis considering various angles of attack. A framework compatible with an SMA constitutive model (implemented as a user material subroutine) is used to perform FSI analysis for multiple flow and configuration cases. A scaled physical model of the high-lift wing is constructed and tested in the Texas A&M 3 ft-by-4 ft (0.91 m-by-1.22 m) wind tunnel. Initial validation of both CFD and FSI analysis is conducted by comparing lift, drag and pressure distributions with experimental results.
  • © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Airframe noise is a significant component of overall noise produced by transport aircraft during landing and approach (low speed maneuvers). A significant source for this noise is the cove of the leading-edge slat. A slat-cove filler (SCF) has been shown to be effective at mitigating slat noise. The objective of this work is to understand the fluid-structure interaction (FSI) behavior of a superelastic shape memory alloy (SMA) SCF in flow using both computational and physical models of a high-lift wing. Initial understanding of flow around the SMA SCF and wing is obtained using computational fluid dynamics (CFD) analysis considering various angles of attack. A framework compatible with an SMA constitutive model (implemented as a user material subroutine) is used to perform FSI analysis for multiple flow and configuration cases. A scaled physical model of the high-lift wing is constructed and tested in the Texas A&M 3 ft-by-4 ft (0.91 m-by-1.22 m) wind tunnel. Initial validation of both CFD and FSI analysis is conducted by comparing lift, drag and pressure distributions with experimental results.

published proceedings

  • 25th AIAA/AHS Adaptive Structures Conference, 2017

author list (cited authors)

  • Scholten, W. D., Patterson, R. D., Hartl, D. J., Strganac, T. W., Chapelon, Q., & Turner, T. L.

complete list of authors

  • Scholten, WD||Patterson, RD||Hartl, DJ||Strganac, TW||Chapelon, QHC||Turner, TL

publication date

  • January 2017