doc: clarify function examples (import)

README.md

@@ -92,6 +92,7 @@ This function can either aggregate multiple polar files into a single structure
 data into a Matlab-ready structure.
 
 ```matlab
+import af_tools.xf2mat
 Polar = xf2mat
 Polar = xf2mat(autosave, trimAoas, inputDir, inputFiles)
 ```
@@ -126,6 +127,7 @@ propellers in off-design configuration (with the Blade Element Momentum Theory
 for instance).
 
 ```matlab
+import af_tools.extendpolar
 [alphaExt, clExt, cdExt] = extendpolar
 [alphaExt, clExt, cdExt] = extendpolar(method, limit, Polar)
 [alphaExt, clExt, cdExt] = extendpolar(method, limit, alpha, cl, cd)
@@ -145,6 +147,7 @@ for instance).
 Determines the camber line of a NACA 4 or 5 digits airfoil.
 
 ```matlab
+import af_tools.nacacamber
 [xc, yc, gradY] = nacacamber
 [xc, yc, gradY] = nacacamber(digits, nPoints, spacing)
 ```
@@ -160,6 +163,7 @@ Determines the camber line of a NACA 4 or 5 digits airfoil.
 Generates the full coordinates of a NACA 4 or 5 digits airfoil.
 
 ```matlab
+import af_tools.nacaairfoil
 [x, y] = nacaairfoil
 [x, y] = nacaairfoil(digits, nPoints, spacing, finiteTrail)
 ```
@@ -173,15 +177,11 @@ Generates the full coordinates of a NACA 4 or 5 digits airfoil.
 
 ### plotpolars
 
-Plots the different polars:
-
-- $`C_l--\alpha`$
-- $`C_d--\alpha`$
-- $`C_m--\alpha`$
-- $`C_l/C_d--\alpha`$
-- $`C_l--C_d`$
+Plots the following polars: $`C_l-\alpha`$, $`C_d-\alpha`$, $`C_m-\alpha`$
+$`C_l/C_d-\alpha`$, $`C_l-C_d`$.
 
 ```matlab
+import af_tools.plotpolars
 plotpolars
 plotpolars(Polar)
 plotpolars(alpha, cl, cd, cm)
@@ -200,6 +200,7 @@ plotpolars(alpha, cl, cd, cm)
 Finds the stall angle of attack and the associated $`C_l`$ and $`C_d`$.
 
 ```matlab
+import af_tools.findstall
 [alpha_s, cl_s, cd_s] = findstall
 [alpha_s, cl_s, cd_s] = findstall(Polar)
 [alpha_s, cl_s, cd_s] = findstall(alpha, cl, cd)
@@ -217,6 +218,7 @@ Finds the stall angle of attack and the associated $`C_l`$ and $`C_d`$.
 Finds the zero-lift angle of attack and the associated $`C_d`$.
 
 ```matlab
+import af_tools.findzerolift
 [alpha_zeroL, cd_zeroL] = findzerolift
 [alpha_zeroL, cd_zeroL] = findzerolift(Polar)
 [alpha_zeroL, cd_zeroL] = findzerolift(alpha, cl, cd)
@@ -235,6 +237,7 @@ Finds the range of angles of attack for which the $`C_l`$ can be considered
 linear.
 
 ```matlab
+import af_tools.findcllinearrange
 [alphaRange, clRange, clSlope] = findcllinearrange
 [alphaRange, clRange, clSlope] = findcllinearrange(Polar)
 [alphaRange, clRange, clSlope] = findcllinearrange(alpha,cl)