*ARCHIVED* development moved to aircraft-studio.
commit to imperial units
Changed files
creator.py
@@ -46,7 +46,7 @@
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def __init__(self, chord, semi_span):
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# Global dimensions
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Removed:
self.chord = chord if chord > 10 else 10
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Added:
self.chord = chord if chord > 40 else 40
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self.semi_span = semi_span
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# mass and area
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self.mass = float()
main.py
@@ -24,8 +24,8 @@
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# Airfoil dimensions
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NACA_NUM = 2412
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CHORD_LENGTH = 100
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Removed:
SEMI_SPAN = 40
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CHORD_LENGTH = 68 # inches
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SEMI_SPAN = 100 # inches
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# Airfoil thickness
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T_UPPER = 0.1
@@ -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