*ARCHIVED* development moved to aircraft-studio.
bugfix
Changed files
creator.py
@@ -198,8 +198,8 @@
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x_chord.extend(i for i in range(x_chord_25_percent, self.chord + 1))
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# Reversed list for our lower airfoil coordinate densification
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x_chord_rev = [i for i in range(self.chord, x_chord_25_percent, -1)]
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Removed:
ext = [i / 10 for i in range(x_chord_25_percent * 10, -1, -1)]
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Removed:
x_chord_rev.extend(ext)
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Added:
extend = [i / 10 for i in range(x_chord_25_percent * 10, -1, -1)]
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Added:
x_chord_rev.extend(extend)
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# Generate our airfoil geometry from previous sub-functions.
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for x in x_chord:
main.py
@@ -23,8 +23,8 @@
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start_time = time.time()
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# Airfoil dimensions
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Removed:
NACA_NUM = 2412
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Removed:
CHORD_LENGTH = 100
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Added:
NACA_NUM = 4412
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CHORD_LENGTH = 133
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SEMI_SPAN = 140
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# Airfoil thickness
@@ -106,7 +106,7 @@
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eval.analysis()
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# eval.info_print(2)
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eval.info_save(SAVE_PATH, _)
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# evaluator.plot_geom(eval)
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evaluator.plot_geom(eval)
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# evaluator.plot_lift(eval)
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# Print final execution time