Abstract:
The configuration of the non-planar staggered-box wing is being
determined by a specified NACA of 0012 which being made by using balsa
wood and aluminium sheet. The effectiveness of the staggered-box is being
tested inside a wind tunnel as there is formation of boundary layer flow.
There parameters that can be collected for the wind tunnel are lift, drag,
temperature, pitching moment, contraction cone speed (CC) and true
airspeed (TS) of the wind tunnel. There will be four different kind of wing that
need to be tested which involved monoplane and non-planar staggered-box
wing. The results are being collected in the form of graph which being
compared among the airfoil wing design to determine the effectiveness
increment of aerodynamic performances.
