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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 0.024 0.020 0.016 0.012 0.008 Drag coefficient 0.004 - --0.05 Moment coefficient --0.1 O Re = 3.1 X 10 O Re = 8.9 X 106 --0.15 -12 -8 -4 12 16 a, degrees Figure 4.11 Experimental data for profile drag coefficient and moment coefficient about the aerodynamic center for the 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.)

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 0.024 0.020 0.016 0.012 0.008 Drag coefficient 0.004 - --0.05 Moment coefficient --0.1 O Re = 3.1 X 10 O Re = 8.9 X 106 --0.15 -12 -8 -4 12 16 a, degrees Figure 4.11 Experimental data for profile drag coefficient and moment coefficient about the aerodynamic center for the 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.)

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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Consider the NACA 2412 airfoil, data for which is given in  4.10 and 4.11. The data are given for two values of the Reynolds number based on chord length. For the case where Rec = 3.1×106, estimate: (a) the laminar boundary layer thickness at the trailing edge for a chord length of 1.5 m and (b) the net laminar skin-friction drag coefficient for the airfoil.

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
0.024 0.020 0.016 0.012 0.008 Drag coefficient 0.004 - --0.05 Moment coefficient --0.1 O Re = 3.1 X 10 O Re = 8.9 X 106 --0.15 -12 -8 -4 12 16 a, degrees Figure 4.11 Experimental data for profile drag coefficient and moment coefficient about the aerodynamic center for the 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.)
Transcribed Image Text:0.024 0.020 0.016 0.012 0.008 Drag coefficient 0.004 - --0.05 Moment coefficient --0.1 O Re = 3.1 X 10 O Re = 8.9 X 106 --0.15 -12 -8 -4 12 16 a, degrees Figure 4.11 Experimental data for profile drag coefficient and moment coefficient about the aerodynamic center for the 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.)
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