ANALISIS AERODINAMIKA DAN KESTABILAN PESAWAT UAV STTA MALE GENERASI 1 DENGAN MENGGUNAKAN XLFR 5

ARDI PERMANA, YUSUP (2018) ANALISIS AERODINAMIKA DAN KESTABILAN PESAWAT UAV STTA MALE GENERASI 1 DENGAN MENGGUNAKAN XLFR 5. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

UAV STTA MALE (Medium Altitude Long Endurance) Aircraft 1 st Generation is UAV created with the Mission of the flight at an altitude of medium and with a distance cruising distances. With a long distance, so it needs high lift and small drag when flying. As well as stability in the UAV aircraft is extremely important as it pertains to the safety of flying. Therefore, this research emphasis is focused on aerodynamics and stability analysis of UAV STTA MALE Aircraft1 st generation using the XFLR 5. Analysis of aerodynamics characteristics was done by varying the angle of attack (α) and side angle (β). While flying on stability of UAV STTA MALE aircraft 1st generation with this Software XFLR5 by showing results in the form of simulated movement. Based on the results of the analysis using XFLR5 Software, it can be concluded that the STTA MALE UAV aircraft 1st generation aerodynamic characteristics with lift force coefficient was 0.455374 and showed that the value of was -0.01078 and the value (CL / CD) max was 122.468 lies at -3 ° attack angle. meets static stability criteria, namely criteria for longitudinal static stability with results , criteria for lateral dimension static stability with results , and directional static stability criteria with results . Stability analysis simulation results obtained root characteristics of longitudinal dimensions, namely: phugoid mode obtained root values-0.0007635 ± 0.3625i and in short period mode obtained the root value of -6.683 ± 17.91i. The lateral directional dimension was obtained: dutch roll mode = -0.7413 ± 9.267i, roll mode = -43.09, and spiral mode = 0.01785. On the lateral dimension the characteristic root value (eigenvalue) was located to the left of the imaginary axis only in dutch roll and roll mode, while in spiral mode the value of the characteristic root (eigenvalue) was to the left of the imaginary axis the longitudinal dimension was to the right of the imaginary axis which means that the aircraft was not dynamically stable in spiral mode

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