Numerical Study On Aerodynamic Interaction Of Propeller And Wing

Since the birth of the first aircraft, the propeller aircraft has been very important as a kind ofaircraft in aviation sector. Nowadays, the turboprop aircraft, which can provide big tens ion and hashigh fuel efficiency, receives more people’s attention. However, the mutual interaction between thepropeller slipstream and wing is very complex, which has a great influence to the aerodynamiccharacteristics. During the preliminary design of the aircraft, it, how to gap a complete analysis anddescription of the interaction between the slipstream and components in the body accurately, is veryimportant for the aerodynamic layout.This thesis applies the accurate simulation of sliding mesh and momentum source method basedon blade element theory to accomplish the numerical study of the model. It compares and analyzes theinterference of the slipstream on the model, including lift and drag characteristics, and aeroperformance of the model, and pressure performance. The sliding mesh method, which moreaccurately calculates the real flow simulation of the propeller/wing, provides a guarantee foranalyzing the slipstream effect particularly. In the Momentum source method, it constructs anequivalent actuator disk model based on the theory of blade element theory, and compiles the programwhich is embedded into the existing Computation Fluid Dynamics (CFD) program. So it provides asimplified model which can economize the time of CFD simulation.By the comparison and analys is of the results based on two methods, it shows that the slipstreamof the propeller alters the flow distribution of the wing/body obviously. It improves the lift and dragcoefficient, makes space velocity flow lines near the propeller appear deflection and apparently bringsdistribution of the low-pressure and high-pressure zones. When simulated the characteristics ofpropeller/wing flow field, the method of sliding mesh has the higher computational accuracy but morecalculation. Nevertheless, the momentum source method has less calculation but lower computationalaccuracy.