S The Experimental Study On A Low Speed Oblique Plate

The conventional aircraft normally adopt the symmetrical configuration. However, the oblique wing aircraft has an asymmetrical configuration with one tip of the wing sweep forward and the other sweep backward. During the transonic and subsonic flight, this asymmetrical configuration has much more advance than the normal symmetrical aircraft in the term of drag reduction. Additionally, the oblique wing aircraft can change its sweep angle easily to have a small ratio aspect in the landing and taking off or low speed cruise and to have a large ratio aspect in the high speed flight. Hence, the oblique wing aircraft could change its configuration to accomplish the flight mission efficiently by adapting the external flight condition actively.As the first step to study the oblique wing aircraft, in this dissertation we study the steady nature of a low speed oblique plate model under different angles of attack and the sweep angles. Using the oil flow method we first study the oil flow pattern on the whole surface of the model. Then using the smoke visualization method, we partially study the spatial flow structure on the plate where we are interested in. Therefore, on one hand, the results derived from the smoke visualization explain the results in the oil flow visualization. On the other hand, the results from oil flow visualization complement the results in the smoke visualization. Hence, using the combined method of oil flow visualization and smoke visualization, we reveal the flow structure around the oblique plate model analytically. Also we acquire the aerodynamic force form the force measurement. Combining the results from the flow visualization, we focus our study on the characteristics of lift and rolling moment. In the end, we explain and interpret the causes of the lift and rolling moment characteristics successfully from the point of flow structure.