Problem 1

Provide a listing of your code and comparison of the results from your code for C_l, C_d, C_df, C_dp, and C_mc/4 with the two examples.

For all the problems below, I am looking for brief, but good, discussion.

Problem 2

The velocity and boundary-layer data files have been provided for Airfoil A at Re of 4.0 million at different angles of attack. Using your computer program, examine how the C_l, C_d, C_df, C_dp, and C_mc/4 vary for this airfoil with alpha. Provide a brief qualitative discussion of the reasons for these variations using plots of these quantities with alpha. In a single figure, plot the variation of V vs. x/c for the different cases (all in the same figure) to aid in your discussion. In another figure, plot Cp vs. x/c for the different cases all on the same figure.

Problem 3

Consider two airfoils B and C at Re of 3.16 million. These two airfoils have different C_mc/4. Use your program to get the C_l, C_d, C_df, C_dp, and C_mc/4 for these two airfoils using the data files provided below. Make a plot of the C_p distributions from the files for these airfoils and discuss how the C_p distribution results in the different pitching moments.

Problem 4

Consider two airfoils D and E at Re of 3.16 million. These two airfoils have different extents of laminar flow. Use your program to get the C_l, C_d, C_df, C_dp, and C_mc/4 for these two airfoils using the data files provided below. Make a plot of the C_p and C_f distributions from the files for these airfoils and discuss how they affect the C_d.

Problem 5

Reconsider airfoil A and let us examine the behavior of this airfoil at two different Re. Use your program to get the C_l, C_d, C_df, C_dp, and C_mc/4 for these two Re using the data files provided below. Make a plot of the C_p and C_f distributions from the files for these airfoils and discuss how they affect the C_d. In particular, identify if there are any laminar separation bubbles and their locations on the upper and lower surfaces of the airfoil at each of the conditions.