Right figure shows the drag polar (CD vs. C) for two wing designs with airfoil, NACA23012...

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Right figure shows the drag polar (CD vs. C₁) for two wing designs with airfoil, NACA23012 (solid line) & NACA631- 412 (dash line). In the plot, there are two group of lines (G & H). One group is smooth surface airfoil and the other group is rough surface airfoil. From the drag polar, answer the following questions (5% each) (a) In group G&H, which is drag source contribute most for CD near CL-0.4? (b) In group G&H, which is drag source contribute most for CD near CL-1.2? (c) Which group of the curves (G or H) is for the airfoils with rough surface? Give the brief reasoning for your answer. (d) In group H, why does the wing design with NACA631-412 airfoil (dash line) has a drag bucket (smaller Cp near CL-0.4) compared with the wing with NACA23012? (e) Which wing design in the plot can lead to the most efficient fuel consumption during cruise flight? Give the brief reasoning for your answer. drag cofficient 032 028- 024- 020- 016- 012- 008- 004- 0- -A O 63,-312 4 Il conflict a 23012 Right figure shows the drag polar (CD vs. C₁) for two wing designs with airfoil, NACA23012 (solid line) & NACA631- 412 (dash line). In the plot, there are two group of lines (G & H). One group is smooth surface airfoil and the other group is rough surface airfoil. From the drag polar, answer the following questions (5% each) (a) In group G&H, which is drag source contribute most for CD near CL-0.4? (b) In group G&H, which is drag source contribute most for CD near CL-1.2? (c) Which group of the curves (G or H) is for the airfoils with rough surface? Give the brief reasoning for your answer. (d) In group H, why does the wing design with NACA631-412 airfoil (dash line) has a drag bucket (smaller Cp near CL-0.4) compared with the wing with NACA23012? (e) Which wing design in the plot can lead to the most efficient fuel consumption during cruise flight? Give the brief reasoning for your answer. drag cofficient 032 028- 024- 020- 016- 012- 008- 004- 0- -A O 63,-312 4 Il conflict a 23012

Answer rating: 100% (QA)

This image shows a drag polar graph which is a plot of drag coefficient Cd versus lift coefficient Cl for two wing designs with NACA National Advisory Committee for Aeronautics airfoil shapes NACA 230... View the full answer