ANALISIS BERBASIS SIMULASI TERHADAP SIFAT AERODINAMIKA AIRFOIL NACA 2412 DENGAN PENAMBAHAN ELEMEN FLAP DAN SLAT
Abstrak
Konsep awal proyek Easy-Fly adalah menciptakan pesawat STOL (Short Takeoff and Landing) yang sangat ringan dengan drag dan kecepatan minimal. Untuk mendukung tujuan ini, CFD (Computational Fluid Dynamics) atau komputasi dinamika fluida diaplikasikan dengan memvariasikan konfigurasi flap dan slat beralur tunggal serta sudut serang pada airfoil NACA 2412. Model viscous yang digunakan dalam kasus ini adalah Spalart-Allmaras. Variasi sudut serang (α) dimodifikasi pada rentang 0°-20°. Untuk model flap, sudut defleksi disesuaikan menjadi 30° dan 40°, dan slat ditambahkan ke konfigurasinya. Berdasarkan hasil penelitian didapatkan bahwa defleksi flap 30° dan 40° menghasilkan nilai CL yang lebih tinggi pada sudut serang 0°. Penggunaan desain flap dan slat pada airfoil NACA 2412 secara efektif menunda pemisahan aliran udara hingga mencapai sudut serang maksimum 24°. Selain desain sistem high-lift pada airfoil NACA 2412, perubahan pada camber dan penyesuaian garis chord efektif menghasilkan peningkatan yang signifikan pada koefisien lift (CL), koefisien drag (CD), dan sudut stall. Akhirnya, defleksi flap 30° lebih efisien daripada defleksi 40° dalam kondisi lepas landas. Rata-rata persentase kenaikan CL/CD dari flap 30° ke 40° adalah 17,61%.
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