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2. Consider an NACA 23015 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level co

use a Reynolds number of 2.6x10^5 to find using graphs

CHAPTER S incompressible Flow over Finite Wings Section lift coefficient - Moment coefficient, -20 -32 -24 -16 8 0 8 16 24 32

Section drag codficity Aceae Momentuetici 343 Sandro Section NACA 2015 Wing Section Figure 5.2Deag coefficient and moment coe

EXAMPLE 4.1 Consider an NACA 2412 airfoil with a chord of 0.64 m in an airstream at standard sea level conditions. The freest

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use a Reynolds number of 2.6x10^5 to find using graphs 2. Consider an NACA 23015 airfoil...
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