For the airfoil with the performance characteristics shown in Fig 17 11, determine the lift and drag at an angle of attack of 10 deg 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 (b) 10 000 m Cz CD ...

For the airfoil with the performance characteristics shown in Fig. 17.11, determine the lift and drag at

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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

(b) 10 000 m.

Cz]CD FÖFD 2.00 t0.40 CD -35 Stall point a =19.6 + 1.50+0.30+F30 -FFD -25 1.00+0.20+20 15 0.50+0.10+ 10 0+0 -5 20 10 15

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Applied Fluid Mechanics

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7th edition

Authors: Robert L. Mott, Joseph A. Untener

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Question Posted: Jan 10, 2019 09:13 AM

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For the airfoil with the performance characteristics shown in Fig. 17.11, determine the lift and drag at

Question:

Cz]CD FÖFD 2.00 t0.40 CD -35 Stall point a =19.6 + 1.50+0.30+F30 -FFD -25 1.00+0.20+20 15 0.50+0.10+ 10 0+0 -5 20 10 15 25 30 Angle of attack, a (deg)

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C L 090 C D 005 Fig1710 A bc 68 m14 m 952 m 2 a At ...View the full answer

Applied Fluid Mechanics

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