| dc.description.abstract | Ribs on aircraft wing components function to hold and distribute the force received by the aircraft wing evenly. When assembling aircraft wing components, the drive rib will be fixed-supported on the spar, so the drive rib will experience a force (load) from its own weight. This study aims to analyze the aerodynamic characteristics of the drive rib to be able to determine the model of lift and angle of attack on the components of the aircraft wing. Another objective is to analyze the maximum stress and safety factor of variations in drive rib components based on the type of material Aluminum Alloy 7010, 7050 T7651 and 7075 T6. The design used in this study is to determine the angles of attack (α) = 0°, 5°, 8°, 10°, 12°, 15°, 16°, 17°, 20° to the optimal limit angle at flight speed conditions v=250 m/s respectively for altitude H=9,000 m, 11,000 m, 13,000 m, 14,000 m, 15,000 m, 16,000 m, 17,000 m, 18,000 m, atmospheric pressure Pa=16,000 Pa, atmospheric temperature Ta=217 K, and the density of air ρ=0.2556 kg/m3. The simulation is carried out by computational fluid dynamic method for successive angles of attack from which the lift value decreases rapidly. The results of the flight altitude test estimate the maximum wing flight altitude of the aircraft, namely Hmax = 16,625.77 m. The maximum stress value received by the drive rib is 45,886 MPa, this value concludes that this value is much smaller than the yield stress of the Aluminum Alloy material of 530 MPa with a safety factor of 10.8. This test method can be used to analyze any aircraft construction. | en_US |
