Create a Python script to construct a BWB cad model

[AlexWrightMAEStrath]

Single taper

• [x] import aerofoil data file
• [x] create sketch from aerofoil points
• [x] scale aerofoil
• [x] clone aerofoil to new position
• [x] add dihedral
• [x] add twist
• [x] add sweep
• [x] loft between sketches/objects
• [x] add winglets

Double taper (centre body and wing)

• [x] create centre body by above process
• [x] add outer wing with different aerofoil
• [x] add winglets Multiple taper
• [x] centre body
• [x] inner wing
• [x] outer wing

[AlexWrightMAEStrath]

FreeCAD issue with lofting between different aerofoil sections: rapid geometry changes cannot be computed. Causes problems at body/wing intersection where it is necessary to change from reflexed centreline aerofoil with limited aft camber to a supercritical section with high aft camber. Similarly, cannot transition from supercritical to symmetrical NACA 4 series at tip/winglet intersection. Second issue - insufficient aerofoil data points across profile when scaled up.

Advice from Dr Fossati:

1. select 1 aerofoil for the whole BWB Done. Comparison of supercritical aerofoil lift, drag & moment coefficients with literature values for optimum BWB configuration {Dommelen & Vos] gave SC20714 as the 'optimum' aerofoil for the outer wing sections. However it is sub-optimal for the centrebody due to the high chord length and significantly different aerodynamic characteristics; higher Reynolds numbers, higher sweep = higher drag div. mach = higher critical mach = delayed shocks.
2. Select 1 body aerofoil and 1 supercritical wing aerofoil. In progress. SC20714 (supercritical) selected for wing. Still to select body aerofoil to satisfy similar criteria.
3. Model winglet separately and introduce a union between the main wing and winglet geometry. In progress.
4. Import aerofoil into python and interpolate curve between points. In progress.