Experimental Investigation of Vortex Flow over an 80 Degree/60 Degree Double Delta Wing at Sideslip

摘要

A series of qualitative and quantitative experimental investigations into the effect of angle of attack and sideslip on the aerodynamic behavior of a sharp leading-edge 80 deg/60 deg double delta wing were conducted. Surface oil-flow and laser light sheet visualizations, as well as surface pressure measurements, were performed on the strake and wing upper surface. The following observations are made. 1) Suction peak increases with increasing angle of attack symmetrically on both sides of the double delta wing before vortex breakdown occurs. 2) Increasing sideslip will cause strong asymmetric vortices over starboard and port sides of the wing, which causes different lift characteristics and as a result causes rolling moment. This may produce difficulties in stability and control of the wing.