ANALISIS AERODINAMIKA PADA AIRFOIL NACA M15 DENGAN PARAMETER GROUND EFFECT MENGGUNAKAN SOFTWARE BERBASIS COMPUTATIONAL FLUID DYNAMICS

Fauzan Haryadi, Muhammad (2022) ANALISIS AERODINAMIKA PADA AIRFOIL NACA M15 DENGAN PARAMETER GROUND EFFECT MENGGUNAKAN SOFTWARE BERBASIS COMPUTATIONAL FLUID DYNAMICS. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

	Text (ABSTRAK) 18040064_ABSTRAK.pdf Download (29kB)
	Text (BAB I) 18040064_BAB I.pdf Download (122kB)
	Text (DAFTAR PUSTAKA) 18040064_DAFTAR PUSTAKA.pdf Download (55kB)
	Text (FULL SKRIPSI) 18040064.pdf Restricted to Repository staff only Download (5MB)

Abstract

As an archipelagic country, Indonesia has crucial problems regarding aspects of inter-island transportation that are important to study. Wing-in-ground (WIG) craft is a solution to the inter-island transportation system because it has better mobility than ships and is cheaper to operate than planes. Thus, a study on the performance of the WIG craft needs to be carried out to determine the suitability aspect of the implementation of the WIG craft. In this study, the effect of changing the angle of attack on the height of the WIG craft on the M15 airfoil was examined. Computational dynamics-based studies were carried out to obtain results where the values of the height and angle of attack were varied. The altitude variation parameter that was studied was in the range of 0.5c to unbound where the variation in angle of attack was 0o to 18o. Airspeed was set to 28 m/s and chord(c) length of 1 m. The S-A based turbulent approach was chosen in the observation of turbulent flow in the airfoil. Furthermore, validation and grid study were also conducted to ensure the validity of the results of this study. From the experimental validation results, the error was 24.92% and 3.00% for CL and CD at the most optimum number of mesh, namely 311121. In the variation of the angle of attack, the highest CL value was obtained at the angle of attack of 16o and at the height of unbound. As for these results, when compared with the CL value at 0.05c, the CL value decreased by 52.03%. On the other hand, the lowest CD value was found at an angle of attack of 2o at the unbound height. When compared to the condition at 0.05c, the CD value decreased by 15.06%. The results of this study were in agreement with previous studies. Moreover, this research in the future will be useful in considering the design and selection of airfoils on WIG-craft.

Actions (login required)

View Item

Downloads