Aerodynamic Study On An Aircraft

Mohd Amerrull, Ismail (2009) Aerodynamic Study On An Aircraft. Project Report. UTeM, Melaka, Malaysia. (Submitted)

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Abstract

Aerodynamic is one of the most important factors for a steady and balance aircraft with an economical fuel usage. Nowadays, many ways or methods were designed to simplify the complicated research in aerodynamic field, especially in vehicle dynamic subject. There are new methods that use simulation study to obtain aerodynamic data for any vehicle design. In this dissertation, the preferred aircraft for the simulation is the stable and unique maneuvering MIG-29 Fulcrum aircraft. This kind of research can give several simulation results data such as drag coefficient, CL and lift coefficient, CD for future research. The first procedure is by designing a model using design software, SolidWorks. Next, transfer the model design to modeler software, COSMOSFloWorks to generate a mesh web for aircraft geometrical volume. Then the solver will solve the problems to get a result connected to certain aerodynamic forces on aircraft that is drag coefficient, CD and lift coefficient, CL. Wind Tunnel Test then performed on the real model, also to get both drag and lift coefficient from the test section. The value of CD and CL obtained for simulation using COSMOSFlowork is 0.087 and 0.019, while CD and CL for Wind Tunnel Test is 0.0102 and 0.0207 respectively. Lastly, compared both methods’ results to find the relationship and differences for the drag coefficient, CD and lift coefficient, CL between COSMOSFloWorks simulation and Wind tunnel Test.

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