Reference no: EM131467
Problem 1
Provide a listing of your code and comparison of the results from your code for Cl, Cd, Cdf, Cdp, and Cmc/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 Cl, Cd, Cdf, Cdp, and Cmc/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 Cmc/4. Use your program to get the Cl, Cd, Cdf, Cdp, and Cmc/4 for these two airfoils using the data files provided below. Make a plot of the Cp distributions from the files for these airfoils and discuss how the Cp 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 Cl, Cd, Cdf, Cdp, and Cmc/4 for these two airfoils using the data files provided below. Make a plot of the Cp and Cf distributions from the files for these airfoils and discuss how they affect the Cd.
Problem 5
Reconsider airfoil A and let us examine the behavior of this airfoil at two different Re. Use your program to get the Cl, Cd, Cdf, Cdp, and Cmc/4 for these two Re using the data files provided below. Make a plot of the Cp and Cf distributions from the files for these airfoils and discuss how they affect the Cd. 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.