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NACA 2412 airfoil Eq. (4.57) 1.6 1.2 Lift coefficient 0.8 0.4 Cm, el4 -0.4 Ед. (4.64) -0.1 Moment -0,8 coefficient -0.2 -1.2 -0.3 O Re = 3.1 X 10 O Re - 8,9 X 106 -0.4 8. 16 24 a, degrees Figure 4.10 Experimental data for lift coefficient and moment coefficient about the quarter-chord point for an NACA 2412 airfoil. (Source: Data obtained from Abbott, I. H., and A. E. von Doenhoff: Theory of Wing Sections, McGraw-Hill Book Company, New York, 1949; also, Dover Publications, Inc., New York, 1959.) Also shown is a comparison with theory described in Section 4.8. go

NACA 2412 airfoil Eq. (4.57) 1.6 1.2 Lift coefficient 0.8 0.4 Cm, el4 -0.4 Ед. (4.64) -0.1 Moment -0,8 coefficient -0.2 -1.2 -0.3 O Re = 3.1 X 10 O Re - 8,9 X 106 -0.4 8. 16 24 a, degrees Figure 4.10 Experimental data for lift coefficient and moment coefficient about the quarter-chord point for an NACA 2412 airfoil. (Source: Data obtained from Abbott, I. H., and A. E. von Doenhoff: Theory of Wing Sections, McGraw-Hill Book Company, New York, 1949; also, Dover Publications, Inc., New York, 1959.) Also shown is a comparison with theory described in Section 4.8. go

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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Consider an NACA 2412 airfoil with a 2-m chord in an airstream with a
velocity of 50 m/s at standard sea level conditions. If the lift per unit span
is 1353 N/m, what is the angle of attack?

NACA 2412 airfoil Eq. (4.57) 1.6 1.2 Lift coefficient 0.8 0.4 Cm, el4 -0.4 Ед. (4.64) -0.1 Moment -0,8 coefficient -0.2 -1.2 -0.3 O Re = 3.1 X 10 O Re - 8,9 X 106 -0.4 8. 16 24 a, degrees Figure 4.10 Experimental data for lift coefficient and moment coefficient about the quarter-chord point for an NACA 2412 airfoil. (Source: Data obtained from Abbott, I. H., and A. E. von Doenhoff: Theory of Wing Sections, McGraw-Hill Book Company, New York, 1949; also, Dover Publications, Inc., New York, 1959.) Also shown is a comparison with theory described in Section 4.8. go
Transcribed Image Text:NACA 2412 airfoil Eq. (4.57) 1.6 1.2 Lift coefficient 0.8 0.4 Cm, el4 -0.4 Ед. (4.64) -0.1 Moment -0,8 coefficient -0.2 -1.2 -0.3 O Re = 3.1 X 10 O Re - 8,9 X 106 -0.4 8. 16 24 a, degrees Figure 4.10 Experimental data for lift coefficient and moment coefficient about the quarter-chord point for an NACA 2412 airfoil. (Source: Data obtained from Abbott, I. H., and A. E. von Doenhoff: Theory of Wing Sections, McGraw-Hill Book Company, New York, 1949; also, Dover Publications, Inc., New York, 1959.) Also shown is a comparison with theory described in Section 4.8. go
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