Analisis Airfoil Double-Slot Flap LS(01)-0417 MOD Dengan Airfoil Tanpa Flap Nasa SC(2) 0610 - Jatisukamto, Gaguk; Sari, Mirna (Jurnal Energi Dan Manufaktur; Vol 11 No 2 (2018): Published in Oktober 2018DO - 10.24843/JEM.2018.v11.i02.p03, 2018)
Kestabilan pesawat terbang ditentukan oleh desain airfoil sayap dan ekor. Perbedaan kecepatan aliran udara antara permukaan atas dan bawah airfoil menghasilkan perbedaan tekanan sehingga akan memberikan gaya angkat (lift) pada sayap. Perbedaan tekanan udara pada permukaan sayap dinyatakan dengan pressure coefficient (C p ), yaitu perbedaan tekanan statik lokal dengan tekanan statik aliran bebas. Koefisien lift (C l ) adalah rasio antara gaya angkat (lift) dengan tekanan dinamis. Peningkatan angka C L sebesar 20,4% pada riset sebelumnya diperoleh berdasarkan simulasi penambahan flap. Tujuan penelitian ini adalah membandingkan hasil simulasi airfoil double slot flap LS(01)-0417 MOD  dengan airfoil NASA SC(2) 0610 yang tanpa flap dan mencari korelasi antara sudut serang (?) dengan koefisien lift (C l ).Metodologi penelitian dilakukan dengan simulasi Computational Fluid Dynamic (CFD). Hasil penelitian dapat disimpulkan bahwa koefisien lift C L untuk airfoil double slot flap LS(01)-0417 MOD menghasilkan C L = 1,498 sedangkan dengan sudut serang ? = 16 o sedangkan airfoil NASA SC(2) 0610 tanpa flap memiliki nilai C L = 1,095 dengan sudut serang 13 o . The stability of the aircraft is ordered by the airfoil design of the wings and the tail. The difference in flow velocity between the surface and the bottom of the airfoil will produce styles that will present lift  on the wings. The difference in airflow velocity between the top and bottom surfaces of the airfoil produces a pressure difference so it will provide lift (lift) on the wing. The lift coefficient ( C L ) is the ratio between lift with dynamic pressure. The difference of air pressure on the wing surface is expressed by pressure coefficient (Cp), the difference of local static pressure with free flow static pressure. The lift coefficient (Cl) is the ratio of lift to dynamic pressure. An increase in C L value of 20.4% in previous research was obtained based on the simulation of flap addition. The purpose of this research is comparison between airfoil double slot flap LS (01)-0417 MOD with airfoil NASA SC (2) 0610 without flap and search between angle of attack (?) with coefficient of lift (Cl). Method research is done by Computational Fluid Dynamic (CFD). The result of this research can be concluded that lift coefficient C L for double slot airfoil flap LS (01)-0417 MOD yield C L = 1,498 while with angle of attack ? = 16 o while airfoil NASA SC (2) 0610 without flap have value C L = 1,095 with angle of attack 13 o