03.2021.138.150

Numerical Investigations of Fluid Structural Interaction for Aircraft Wing Flap Structure Using CFD Technique

Author(s):

Ali Al-Zughaibi, Emad Q. Hussein, Farhan Lafta Rashid

Affiliation(s):

College of Engineering, University of Kerbala-Iraq

Corresponding Author Email: emad.dujaily@uokerbala.edu.iq

This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Fluid-structure interaction plays a vital role and influences system design. The purpose of this paper is to present a robust strategy of investigating the effect of flap geometry on structure analysis of NACA 23012 airfoiled flying wing. The proposed model has been tested with three configurations, 20% C, 30% C and 40% C of the single plain flap at an effective specific Reynold’s number (Re) beneath subsonic fluid flow condition. The simulated model has been solved the governing equations such as: Continuity, Reynolds Averaging Never-Stokes, and Energy Equation. Thus, in cooperative with analysis of dynamic meshing technique to predict the wing pressure distribution through variation of flap angles and setting Angle of Attack (AoA). The induced equivalent von- Mises stress and the total deformation according to the flow has been successfully computed using the ANSYS program. As a result, the stress and deformation increment highly relative to a larger flap chord. The maximum value of stress is 40% greater than others, while the maximum deflection is 45%, thus, it should be considered within wing design. It is eventually seen that the average pressure distribution over airfoil increases relative to growth in the flap angle for all cases. The maximum value of average pressure was found at the flap angle approximated to . The maximum value of stress (100.03 MPa) was found at the root of the wing relative to the maximum bending moment occurs at the root. So, the maximum deflection occurs at the free side of the tip wing at (301.35 mm). The comparison of the pressure coefficient with the previous measurement is performed to prove the effectiveness and reality of the CFD simulates model.