From 867c939ca999daa69b41dae131e39bcbc5eecb70 Mon Sep 17 00:00:00 2001
From: Thomas Lambert <t.lambert@uliege.be>
Date: Wed, 7 Jun 2023 22:18:18 +0200
Subject: [PATCH] refact(polargen): tweak polar generator script
---
src/airfoil_data/polargenerator.py | 19 +++++++++++++------
1 file changed, 13 insertions(+), 6 deletions(-)
diff --git a/src/airfoil_data/polargenerator.py b/src/airfoil_data/polargenerator.py
index cac3d57..5e83e57 100755
--- a/src/airfoil_data/polargenerator.py
+++ b/src/airfoil_data/polargenerator.py
@@ -1,3 +1,4 @@
+#!/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,
--
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