NAVWEPS OD-801-80 
HIGN SPEED AEQODYNAMICJ 
WING IN TRANSONIC FLOW 
I M = .700 a= +2O CL= ,370 
NO SHOCK WAVES 
I 
I M-.800 a=+2O CL=.442 
SHOCK FORMATION IS APPARENT AT 
25 TO 30 % CHORD POSITION 
I M=.075 a=+20 CL=.450 
SHOCK INDUCED SEPARATION ALONG 
AFT PORTION OF WING PLAPJFORM 
Figure 3.9. Transonic Flow Patterns (sheet 2 of 2)