Recent Progress in the Calculation of Potential Flows 



FLAP ANGLE 45' (^NACA 230V2 



30C 



200 



1 00 



DISTANCE TRAVELED (LEADING EDGE) 



flap angle 

 'naca 



(a) Wake shapes at two different times 



POINT OF ROTATION 



(b) Calculated pressure distribution when 

 the flap is at maximum deflection (45°). 

 The steady-state result is also shown in 

 (b). Rearward movement of flap has in- 

 creased chord by 4.7%. 



Fig. 10 - Calculated results for an NACA 

 Z301Z airfoil with a flap undergoing simple - 

 harmonic rotational motion of angular - 

 range amplitude 45° . 



337 



