Validation and verification of aerodynamics loading of Schrenk Approximation, Prandtl Lifting-Line and Computational Fluid Dynamics with experiment on NACA series

Nur Nabillah Mohd Kamal ； Adi Azriff Basri ； Ernnie Illyani Basri ； Mohammed Thariq Bin Haji Hameed Sultan ； Azmin Shakrine Mohd Rafie ； Mohd Faisal Abdul Hamid

《Journal of Aeronautics, Astronautics and Aviation》 53卷2期 Vol.53 No.2 ISSA 2020 Special Issue (2021/06) Pp. 283-288

https://doi.org/10.6125/JoAAA.202106_53(2).21

摘要

The shape of an airfoil helps in minimizing pressure distribution on the wing where the lift force is generated as the air moving faster towards the top surface of the wing. Schrenk Approximation Method and Prandtl Lifting-Line Theory are useful in estimating the aerodynamics load of the wing at the early stage of the design process. Whilst, Computational Fluid Dynamics (CFD) method is a modern alternative to a wind tunnel test that provides a great accuracy result. Yet, the experimental method still holds the highest reliability compared to the others. A comparison of Schrenk method, Prandtl method, CFD and experiment in estimating the aerodynamic load at a 0-degree angle of attack is conducted on NACA 4415 airfoil wing. The goal of this study is to determine the aerodynamic performance of the selected wing and to acquire the percentage difference of lift coefficient and lift force between all four approaches. From the study, the Prandtl's method and CFD show a slight percentage difference compared to the experiment with the percentage obtained of 23% and 2% for lift coefficient and lift force, respectively. Whereas, Schrenk provides the highest percentage difference among all approaches with a 42% difference for both lift coefficient and lift force.

關鍵字

Schrenk Approximation method ； Prandtl Lifting-Line Theory ； Experimental ； CFD ； Airfoil

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