Draft: Set aero default #666
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…aero.py and table_based.py
…sed/test/test_solved_aero_group.py will fail.
…craft.HorizontalTail.SWEEP = 0 in gaspaero.py and basic_calculations.py
…10.13, but keep Aircraft.HorizontalTail.SWEEP = 25.0
…COEFFICIENT_INCREMENT, Aircraft.Fuselage.FLAT_PLATE_AREA_INCREMENT, Aircraft.Design.DRAG_COEFFICIENT_INCREMENT, Aircraft.Fuselage.FLAT_PLATE_AREA_INCREMENT, Aircraft.Wing.MIN_PRESSURE_LOCATION to default in AeroGeom of gaspaero.py
…UBSONIC_DRAG_COEFF_FACTOR, Aircraft.Design.SUPERSONIC_DRAG_COEFF_FACTOR, Aircraft.Design.LIFT_DEPENDENT_DRAG_COEFF_FACTOR, Aircraft.Design.ZERO_LIFT_DRAG_COEFF_FACTOR to defaults in DragCoefClean of gaspaero.py
…aft.Wing.THICKNESS_TO_CHORD_ROOT, Aircraft.Wing.SPAN, Aircraft.Wing.SLAT_CHORD_RATIO to default in BasicFlapsCalculations of basic_calculations.py
…_DEFLECTION, Aircraft.Wing.ROOT_CHORD, Aircraft.Fuselage.LENGTH, Aircraft.Wing.LEADING_EDGE_SWEEP, Aircraft.Wing.SLAT_SPAN_RATIO to default in BasicFlapsCalculations of basic_calculations.py
…ENT_OPTIMUM, Aircraft.Wing.LOADING to defaults in Cl_max.py
…VISCOSITY, and Dynamic.Atmosphere.MACH using add_aviary_input and add_aviary_output.
…G_INCREMENT_OPTIMUM to defaults.
….Wing.SLAT_LIFT_INCREMENT_OPTIMUM Aircraft.Wing.FLAP_CHORD_RATIO to defaults.
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Summary
A draft
Related Issues
Backwards incompatibilities
None
New Dependencies
None