supersonic flow patterns of figure 3.19. Trail- 
ing edge control surfaces can be affected ad- 
versely by the shock waves formed in flight 
above critical Mach number. If the airflow 
is separated by the shock wave the resulting 
buffet of the control surface can be very objec- 
tionable. In addition to the buffet of the sur- 
face, the change in the pressure distribution due 
to separation and the shock wave location can 
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