*ARCHIVED* development moved to aircraft-studio.
top stringer amount
main.py
@@ -24,7 +24,7 @@
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# Airfoil dimensions
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NACA_NUM = 2412
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Removed:
CHORD_LENGTH = 101
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Added:
CHORD_LENGTH = 100
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SEMI_SPAN = 40
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# Airfoil thickness
@@ -37,11 +37,11 @@
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STRINGER_MASS = 5 # lbs
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# Area
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Removed:
SPAR_CAP_AREA = 0.0 # sqin
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Added:
SPAR_CAP_AREA = 0.3 # sqin
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STRINGER_AREA = 0.1 # sqin
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# Amount of stringers
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Removed:
TOP_STRINGERS = 3
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Added:
TOP_STRINGERS = 6
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BOTTOM_STRINGERS = 4
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NOSE_TOP_STRINGERS = 3
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NOSE_BOTTOM_STRINGERS = 6