Numerical Analysis of Slipstream Effect Propeller On

• Main Author: Safitri - Nim: 13613038, Inggi
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/22584
• Institution: Institut Teknologi Bandung

Slipstream effect is a complex aerodynamic phenomenon that occurs behind the propeller. This phenomenon arises from the rotation of the blade propeller. The slipstream effect can make the flow that flows into the wing or tail, thereby reducing the effectiveness of the component. The magnitude of the slipstream effect caused by the propeller and influenced by several factors, one of them is the angular velocity propeller. The design angular velocity used in this research is 2700 RPM. Variations are made on off-design angular velocity at 2300 RPM, 2500 RPM, 2900 RPM, and 3100 RPM. Research on slipstream effect is done in several methods, they are steady state and unsteady state (transient) CFD numerical simulation method, and analytic approach. In the steady state approach frozen rotor interface is used, while unsteady state simulation uses transient conditions. The simulation method shows that the effect of flow slipstream on propeller on condition causes suction on lower wing and causes the distribution of speed increase behind the propeller. The performance value of thrust coefficient and power coefficient propeller inversely proportional to propeller angle velocity. There is a difference in the value of propeller performance of analytic and numerical results due to differences in assumptions used. Such assumptions include air viscosity and hub or spinner interference not taken into account in analytic approaches, as well as the presence of Reynold number variations occurring along the blade.