Question

Lab_data.xlsx contains the experimental drag force data for three different aerofoils- flat plate, symmetric and cambered. The drag co-efficient ($C_D$) can be calculated from the following equation, $C_D = \frac{2F_D}{\rho v^2 S}$ Here, $F_D$ (N) is the drag force, $\rho$ ($kgm^{-3}$) is the air density, $v$ ($ms^{-1}$) is the air velocity and S($m^2$) is the reference area. Assume that $\rho = 1.205 kgm^{-3}$, $v = 25 ms^{-1}$ and $S = 0.02011 m^2$. (a) Import the data from the \"Lab_data.xlsx\" in a MATLAB script. Assign different variables for each aerofoil. (b) Create a function named, \"drag_calc\" that accepts $F_D$, $\rho$, $v$ and $S$ as input arguments and computes the $C_D$ value. An example of the function header can be, function Cd = drag_calc(Fd, rho, V, S). (c) Call the function in your MATLAB script to calculate the co-efficient ($C_D$) for all aerofoils. Plot the $C_D$ values for all aerofoils against the angle of attack ($\alpha$) in the same figure. Use different colour symbols for each aerofoil to identify the trend of the drag-coefficients. Include figure title, axis-labels, and appropriate legends. (d) Calculate the minimum drag force and the corresponding angle of attack for all aerofoils using MATLAB in-built min() function. (e) Print the minimum drag co-efficient $C_D$ for each aerofoil and the corresponding angle of attack ($\alpha$) values by using fprintf().

          Lab_data.xlsx contains the experimental drag force data for three different aerofoils- flat plate, symmetric and
cambered. The drag co-efficient ($C_D$) can be calculated from the following equation,
$C_D = \frac{2F_D}{\rho v^2 S}$
Here, $F_D$ (N) is the drag force, $\rho$ ($kgm^{-3}$) is the air density, $v$ ($ms^{-1}$) is the air velocity and S($m^2$) is the reference area.
Assume that $\rho = 1.205 kgm^{-3}$, $v = 25 ms^{-1}$ and $S = 0.02011 m^2$.
(a) Import the data from the \"Lab_data.xlsx\" in a MATLAB script. Assign different variables for each aerofoil.
(b) Create a function named, \"drag_calc\" that accepts $F_D$, $\rho$, $v$ and $S$ as input arguments and computes the $C_D$ value. An
example of the function header can be,
function Cd = drag_calc(Fd, rho, V, S).
(c) Call the function in your MATLAB script to calculate the co-efficient ($C_D$) for all aerofoils. Plot the $C_D$ values for all
aerofoils against the angle of attack ($\alpha$) in the same figure. Use different colour symbols for each aerofoil to identify the
trend of the drag-coefficients. Include figure title, axis-labels, and appropriate legends.
(d) Calculate the minimum drag force and the corresponding angle of attack for all aerofoils using MATLAB in-built min()
function.
(e) Print the minimum drag co-efficient $C_D$ for each aerofoil and the corresponding angle of attack ($\alpha$) values by using
fprintf().

Labdata.xlsx contains the experimental drag force data for three different aerofoils- flat plate, symmetric and
cambered. The drag co-efficient (CD) can be calculated from the following equation,
CD = (2FD)/(ρ v^2 S)
Here, FD (N) is the drag force, ρ (kgm^-3) is the air density, v (ms^-1) is the air velocity and S(m^2) is the reference area.
Assume that ρ = 1.205 kgm^-3, v = 25 ms^-1 and S = 0.02011 m^2.
(a) Import the data from the L̈abdata.xlsxïn a MATLAB script. Assign different variables for each aerofoil.
(b) Create a function named, d̈ragcalcẗhat accepts FD, ρ, v and S as input arguments and computes the CD value. An
example of the function header can be,
function Cd = dragcalc(Fd, rho, V, S).
(c) Call the function in your MATLAB script to calculate the co-efficient (CD) for all aerofoils. Plot the CD values for all
aerofoils against the angle of attack (α) in the same figure. Use different colour symbols for each aerofoil to identify the
trend of the drag-coefficients. Include figure title, axis-labels, and appropriate legends.
(d) Calculate the minimum drag force and the corresponding angle of attack for all aerofoils using MATLAB in-built min()
function.
(e) Print the minimum drag co-efficient CD for each aerofoil and the corresponding angle of attack (α) values by using
fprintf().

Added by Soledad H.

Question

Please give Ace some feedback