17.30) For the airfoil with the performance characteristics shown  in Fig. 17.11 , determine the lift and drag at an angle of  attack of 10°. The airfoil has a chord length of 1.4 m and  a span of 6.8 m. Perform the calculation at a speed of  200 km/h in the standard atmosphere at (a) 200 m and  (b) 10 000 m

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Chapter8: Momentum And Collisions
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17.30) For the airfoil with the performance characteristics shown 
in Fig. 17.11 , determine the lift and drag at an angle of 
attack of 10°. The airfoil has a chord length of 1.4 m and 
a span of 6.8 m. Perform the calculation at a speed of 
200 km/h in the standard atmosphere at (a) 200 m and 
(b) 10 000 m. 
 

FIFD
2.00 f0.40-
Cp
35
Štall point
a = 19.6°
1.50 +0.30-30
CL
FIFD
25
1.00 +0.20
20
15
0.50 f0.10
10
0+0
-5
5
10
15
20
25
30
Angle of attack, a (deg)
FIGURE 17.11 Airfoil performance curves.
Transcribed Image Text:FIFD 2.00 f0.40- Cp 35 Štall point a = 19.6° 1.50 +0.30-30 CL FIFD 25 1.00 +0.20 20 15 0.50 f0.10 10 0+0 -5 5 10 15 20 25 30 Angle of attack, a (deg) FIGURE 17.11 Airfoil performance curves.
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