A wing with a NACA 23015 airfoil profile has an aspect ratio of 10 and a...

 

  

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A wing with a NACA 23015 airfoil profile has an aspect ratio of 10 and a taper ratio of 0.6. The lift coefficient chart for the NACA 23015 airfoil can be found on page 425 of the text. The required CL is 0.75. Assume that t = 8. Find: The induced drag coefficient (2 pts) a. b. The wing lift slope (2 pts) The geometric angle of attack (2 pts) С. Remember to use the proper units (radians or degrees) for each equation. 3.6 3.2 2.8 2.4 2.0 1.6 1.2 438 /1131 0. -4 -8 -1.2 -4 -1.6 -2.0 -32 -24 -16 -8 8 16 24 32 Section angle of attack, ap, deg. NACA 23015 Wing Section Figure 5.2a Lift coefficient and moment coefficient about the quarter-chord for the NACA 23015 airfoil. Moment coefficient, c Section lift coefficient, e A wing with a NACA 23015 airfoil profile has an aspect ratio of 10 and a taper ratio of 0.6. The lift coefficient chart for the NACA 23015 airfoil can be found on page 425 of the text. The required CL is 0.75. Assume that t = 8. Find: The induced drag coefficient (2 pts) a. b. The wing lift slope (2 pts) The geometric angle of attack (2 pts) С. Remember to use the proper units (radians or degrees) for each equation. 3.6 3.2 2.8 2.4 2.0 1.6 1.2 438 /1131 0. -4 -8 -1.2 -4 -1.6 -2.0 -32 -24 -16 -8 8 16 24 32 Section angle of attack, ap, deg. NACA 23015 Wing Section Figure 5.2a Lift coefficient and moment coefficient about the quarter-chord for the NACA 23015 airfoil. Moment coefficient, c Section lift coefficient, e