#TITLE_ALTERNATIVE#

• Main Author: MAHESA AKBAR (NIM : 13605049); Tim Pembimbing : Dr. Leonardo Gunawan ; Ir. Muhammad Kusni, M.T.
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/16333
• Institution: Institut Teknologi Bandung

Accurate prediction of unsteady aerodynamics loads is an essential part of solving aeroelasticity problems. This accurate estimation is required in aircraft design as it is related directly to the prediction of the dynamic response and the stability which determine the maximum flight speed (flutter speed), the flight envelope and other important parameters. Significant research has been performed in the past in analytical, numerical and experimental aspects of the aeroelasticity problem in subsonic, transonic and supersonic flows. Such investigations are still going on in an effort to improve the accuracy and efficiency of the prediction methods for more complicated aerodynamic configurations ranging from two dimensional thin airfoils to full aircraft configurations. <br /> <br /> <br /> <br /> <br /> In the present work, the Doublet Point Method (DPM) of Ueda and Dowell in 1982 was reformulated and implemented on a numerical code. The reformulation process consisted of the verification of the pressure – downwash formulation which was proposed by Kussner in 1935 [13] and the transformation of the pressure-downwash formula into the discrete element method by Ueda and Dowell in DPM. The method was then implemented as a MATLAB computer code which is proposed for predicting the aerodynamic load for planar lifting surface (wing) in unsteady subsonic flow. This code can then be used as a base to develop a more accurate method. <br /> <br /> <br /> <br /> <br /> To validate the method and the numerical procedure, the code was used to calculate the unsteady aerodynamics load of oscillating BAH wing [2] and CN 235 [10]. The results were in good agreements qualitatively and quantitatively with those obtained by other researchers.