Determine the required wing area for a 1350 kg airplane to cruise at 125 km h if the airfoil is set at an angle of attack of 2 5 deg The airfoil has the characteristics shown in Fig 17 11 The cruise altitude is 5000 m in the standard atmosphere Cz CD FFD 2 00 t0 40 CD 35 Stall point a 19 6 1 50 0 3...

Determine the required wing area for a 1350-kg airplane to cruise at 125 km/h if the airfoil

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Determine the required wing area for a 1350-kg airplane to cruise at 125 km/h if the airfoil is set at an angle of attack of 2.5°. The airfoil has the characteristics shown in Fig. 17.11. The cruise altitude is 5000 m in the standard atmosphere.

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

ISBN: 978-0132558921

7th edition

Authors: Robert L. Mott, Joseph A. Untener

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Question Posted: Jan 10, 2019 09:12 AM

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Determine the required wing area for a 1350-kg airplane to cruise at 125 km/h if the airfoil

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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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