NAVWEPS 00-802-80 
APPLICATION OF AERODYNAMICS 
TO SPECIFIC PROBLEMS OF FLYtNG 
AIRPLANE OUT OF 
GROUND EFFECT TIP VORTEX 
/ 
REDUCED DOWNWASH 
AND UPWASH- REDUCED t-- SFkAN’ --I 
PERCENT 
REDUCTION 
IN 
INDUCED 
DRAG 
COEFFICIENT 
LIFT 
COEFFICIEN’ 
CL 
40 
CL CONSTANT 
30 
20 
IO 
0 
r 
1 
RATIO OF WING HEIGHT TO SPAN, h/b 
AIRPLANE IN 
THRUST 
REQ’D 
LBS. 
AIRPLANE OUT OF 
GROUND EFFECT 
w - w 
ANGLE OF ATTACK, 0 VELOCITY, KNOTS 
Figure 6.9. Ground Effect 
380 
AIRPLANE OUT OF / 
(-,’ < AIRPLANE IN 
GROUND EFFECT