Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Aerospace Engineering

In the present thesis, Chapter 1 is an introduction to the propulsive wing and literature review of related work done in this field. In Chapter 2 the numerical model and method of calculation and the grid sensitivity analysis is presented. In Chapter 3 the results is shown. In Chapter 4 the conclusion is discussed. The propulsive wing is examined numerically to determine the benefit and efficiency of a new proposed propulsive device. In the propulsive wing concept, the fan is embedded inside the wing section and the out flow jet blows over the wing. This pushes the aerodynamic envelope of the wing by avoiding stall up to 45o and hence maintain very high lift coefficient. The numerical model is first compared with published experimental data. The comparison shows that the K-{uF065} model is the optimum model for the numerical calculation; a sensitivity study is then performed to determine the flight operating points of the propulsive wing based on the numerical values for the net thrust force. The numerical results show that the operating speed of the propulsive wing increases from 3.4 to 13.5 m/s as the RPM throttle setting increases from 1020 to 4200 RPM. The lift can be high as 23 N for {uF061} = 30o, which is not attainable with conventional wings. The airstream operating velocity (velocity required to get almost zero net thrust, is proportional to the fan speed at the same angle of attack, while it is proportional inversely with the RPM at different angles of attack; at 4200 RPM, the velocity is 21.6 m/s at ({uF061}=0o) while it decreases to 13.5 m/s at ({uF061}=30o).The relation between Lift and the fan RPM{u2019}s is progressively proportioned, the lift increases with RPMs in same angle of attack, and also it increases with angles of attack for same RPM

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