u03c1 u2062 u2062 v 2 u2062 s u03c1 fluid u2062 u2062 density v flow u2062 u2062 velocity and s platform u2062 u2062 area u2062 u2062 of u2062 u2062 wing u2062 for translational element with a height of 0 01 c and position of 0 05 c forward of the trailing edge wherein c chord line 30 shows the characteristics with the translational element deployed downward line 32 shows the characteristics with the translational element retracted and line 34 depicts the characteristics with the translational element deployed upward as can be seen a translation element with a height of one percent of the chord deployed downward near the trailing edge is demonstrated to increase the lift at zero angle of attack by approximately 35 note in fig3 through fig6 that airfoil 10 employs a tapered or sharp trailing edge 28 and that the translational elements are positioned forward of the trailing edge 28 alternatively airfoil 10 could employ a blunt trailing edge 36 as shown in fig8 through fig1 in fig9 translational element 26 is shown in an upward extended position to cause a decrease in lift in fig1 translational element 26 is shown in a fully retracted position which would be the case during aircraft cruise conditions in fig1 translational element 26 is shown in a downward extended position to cause an increase in lift it will be appreciated that the specific implementation of the translational elements will vary with the scale of the lifting surface for example.