Conceptual Design and Optimization of Distributed Electric Propulsion General Aviation Aircraft

The interaction between the slipstream of propellers and wing an aircraft with distributed electric propulsion (DEP) could benefit aerodynamics. A conceptual design optimization are carried out in order to increase range general aviation without affecting its takeoff landing velocity same fuselage condition. Propellers modelled using actuator disk (AD) theory, is vortex lattice method (VLM) obtain DEP aircraft’s aerodynamics design. DIRECT used for global optimization. To concentrate on layout wing, a propeller chord distribution, twist number blades selected. objective achieving maximum product lift–drag ratio efficiency under force balance constrains. Additionally, decrease distance, performance optimized smallest at angle near tail down constrains acceleration bigger than 0 Mach tip smaller 0.7. CFD simulation was confirm pretty accurate Compared reference aircraft, improved 10 high-lift leading edge 2 wing-tip may boost cruise by 6% while maintaining velocity. Furthermore, it has been shown that stall speed wings would rise proportionally when compared conventional power need will be increased as result operation propellers. optimal approach suggested this work some value research fixed-wing aircraft.