6. (4) Calculate the lift to drag ratio (n) for the airfoil in figure 1 (end of exam) at a 15° angle of attack. a. b. .45 1.375 .672 с. 15 d. .07 e. 11 -1 -7.

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6. (4) Calculate the lift to drag ratio (n) for the airfoil in figure 1 (end of exam) at a 15° angle of
attack.
a.) 2.1
b. .45
c. 15
1.375
675
d. .07
e. 11 -1
Transcribed Image Text:6. (4) Calculate the lift to drag ratio (n) for the airfoil in figure 1 (end of exam) at a 15° angle of attack. a.) 2.1 b. .45 c. 15 1.375 675 d. .07 e. 11 -1
DRAC
COEFFICIENT
30
25
10
20
COEFEIUTENT
Geopotential Height (km)
LIFT
Clark Y airfoll at aspect ratio=6
-1.50-
.30
1.25-
.25
.20
00.
.75
.15
.50
.10
-.25
.05
0.
-5
-10
15
20
5.
ANGLE OF ATTACK
Figure 1: coefficient of lift and drag vs. angle of attack.
Standard Atmosphere Density
16
14-
12
10
8.
6.
4
Transcribed Image Text:DRAC COEFFICIENT 30 25 10 20 COEFEIUTENT Geopotential Height (km) LIFT Clark Y airfoll at aspect ratio=6 -1.50- .30 1.25- .25 .20 00. .75 .15 .50 .10 -.25 .05 0. -5 -10 15 20 5. ANGLE OF ATTACK Figure 1: coefficient of lift and drag vs. angle of attack. Standard Atmosphere Density 16 14- 12 10 8. 6. 4
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