This tool helps visually explore how changes to wing geometry and basic aircraft parameters affect the front profile and conceptual aerodynamic indices. The visual indicators show the *percentage difference* or *relative change towards an optimum* for "Total Drag," "Roll Stability," "Adverse Yaw," "Thermal Turn Stability," and "Air Penetration" relative to a baseline configuration. It's designed for educational and comparative understanding.

Major Assumptions & Simplifications:

• Simplified Indices & Relative Comparisons: The "Roll Stability," "Adverse Yaw," "Thermal Turn Stability," and "Air Penetration" indices are highly abstract. "Total Drag" is calculated based on simplified aerodynamics. **The displayed percentages indicate relative change, not absolute performance values.**
• Wing Area Estimation: Wing area is estimated for a tapered wing using the root chord, wingspan, and an assumed taper ratio of 0.45 (TipChord = RootChord * 0.45).
• Reference Airspeed: Lift coefficient is calculated assuming a fixed reference airspeed of 12.0 m/s (approx 43.2 km/h or 26.8 mph) to maintain Lift = Weight. Drag is then calculated at this speed.
• Parasite Drag: Influenced by geometric factors in an illustrative way, modifying a base parasite drag coefficient of 0.02.
• Oswald Efficiency (e): Assumed constant at 0.8.
• Adverse Yaw Index: Conceptually influenced by wingspan, effective dihedral, and tip joiner angle. Does not model ailerons or true yawing moments.
• Thermal Turn Stability Index: Conceptually aims for an optimal balance of dihedral and other factors for ease of maintaining a bank in thermals. Not a direct measure of spiral stability in the classical engineering sense. An optimal index value is targeted.
• Air Penetration Index: Conceptually represents the ability to fly efficiently against the wind, influenced by wing loading and total drag coefficient at the reference airspeed.
• Chord-to-Span Ratio Warning: The root chord input field will highlight if the ratio of root chord to wingspan becomes unconventionally shallow (<0.03) or deep (>0.18).
• No Airfoil/Planform Detail: Does not include specific airfoil data, Reynolds/Mach effects beyond the simplified parasite drag, detailed top-view planform geometry (beyond the assumed taper), or wing twist.
• Static Geometry: Models the un-deflected wing shape; control surface deflections are not considered.
• No Structural/Full Stability Analysis: Ignores structural integrity, detailed longitudinal/directional stability beyond the conceptual roll stability index.

Disclaimers:

• Not for Direct Engineering or Flight-Critical Decisions: The simplified outputs are **not suitable for making final engineering decisions for building, modifying, or flying any aircraft.**
• Illustrative Only: Visuals and percentage differences are conceptual and relative.
• No Guarantee of Quantitative Accuracy: Percentage differences do not reflect precise, actual aerodynamic performance figures.
• Consult Experts: For any aircraft design or modification, always consult qualified professionals.

This software is provided "as is", without warranty of any kind, express or implied, including but not limited to the warranties of merchantability, fitness for a particular purpose and noninfringement. In no event shall the authors or copyright holders be liable for any claim, damages or other liability, whether in an action of contract, tort or otherwise, arising from, out of or in connection with the software or the use or other dealings in the software.

This tool is for educational and illustrative purposes only.