جستجوی مقالات مرتبط با کلیدواژه "horizontal tail" در نشریات گروه "فنی و مهندسی"

The main goal of this research is to study of interaction between the propulsion system and the WIG Craft main parts. Therefore, the effects of some parameters such as the propeller rotation direction and the propulsion system location on the aerodynamic quality of the WIG craft have been studied deeply. Using ANSYS-CFX Software, The SIMPLE algorithm has been utilized to consider the pressure-velocity coupling, additionally the k-ω SST model has been applied as a turbulence model to take the account of the flow separation. The numerical approach is verified by comparing its results with experimental data of a three-blade aerial propeller. These comparisons indicated that there was a good agreement between present numerical results and experimental ones. The results revealed that the propeller rotation direction has no significant effect on the aerodynamic quality of the WIG craft and at α=3o, the highest aerodynamic quality is achieved. Moreover, as the propulsion system approached closer to the WIG craft center line, the drag and lift forces on the horizontal tail are respectively enhanced and decreased, subsequently in this situation the longitudinal stability of the vehicle is decreased; whereas by changing the vertical position of the propulsion system, the drag and lift forces on the horizontal tail are correspondingly reduced and increased, Thus the longitudinal stability of the WIG craft is increased.

In this research, a dynamic simulator software has been designed to calculate the time varying load factor acting on an aircraft wing and on a horizontal tail relation to elevator deflection angle. The related loading equations were extracted and solved by MATLAB software and were presented as a GUI software. By introducing time varying angles of the elevator deflection in each flight maneuver and the necessary derivatives, the dynamic load factor on the wing and on horizontal tail were calculated with respect to time. In derivation of equations, the moment due to elevator camber, the effect of time lag in downwash, and the change in tail angle due to rotation were also considered. Comparing the results with the analytical ones confirms the reliability of the software. This software provides a rational approach in aircraft loading calculations that is applicable for structural design of the wing and the horizontal tail, as well as for conformity with the requirements of aviation regulations for loading, to obtain an airworthiness certificates.