refact(polargen): tweak polar generator script

src/airfoil_data/polargenerator.py

+#!/usr/bin/python3
 """Generate airfoil polars automatically using XFOIL
 
  Rotare requires the input of airfoil polars to interpolate properly the lift
@@ -27,25 +28,30 @@ import os
 import numpy as np
 import aeropy.xfoil_module as xf
 
+# Defaults for polar generation
+# AOA
+REYNOLDS = [re * 1000000 for re in [0.02, 0.1, 0.2, 0.5, 1, 2, 5, 10]]
+AOA = list(np.arange(-16, 22, 0.5))
+MACH = 0.1
+
 
 def main():
     """Creates polar files for each reynolds"""
 
     airfoil = parse_inputs()
-    reynolds = [re * 1000000 for re in [0.2, 0.5, 1, 1.5, 2, 5, 10]]
-    aoa = list(np.arange(-18, 25, 0.5))
 
     i = 1
-    for re in reynolds:
-        print("%d/%d - Calculating polar for Re=%ge6" % (i, len(reynolds), re / 1e6))
+    for re in REYNOLDS:
+        print("%d/%d - Calculating polar for Re=%ge6" % (i, len(REYNOLDS), re / 1e6))
         i = i + 1
 
         if airfoil.startswith("naca"):
             xf.call(
                 airfoil,
-                alfas=aoa,
+                alfas=AOA,
                 output="Polar",
                 Reynolds=re,
+                Mach=MACH,
                 plots=False,
                 NACA=True,
                 iteration=500,
@@ -54,9 +60,10 @@ def main():
             if os.path.exists(airfoil) or os.path.exists(airfoil + ".dat"):
                 xf.call(
                     airfoil,
-                    alfas=aoa,
+                    alfas=AOA,
                     output="Polar",
                     Reynolds=re,
+                    Mach=MACH,
                     plots=False,
                     NACA=False,
                     iteration=500,