Optimization Wizard

Wing Design Advisor

Input your cruise target lift, drag, and velocity values below. The solver will calculate structural dimensions and rank airfoil compatibility in real time.

Optimization Dashboard

Wing Design & Airfoil Advisor.

Modify the design parameters, flight targets, and mission constraints below. The recommendation engine and layout calculators will update in real time without page refreshes.

Design Inputs

Application Type

Lift Coefficient (C_L)

Drag Coefficient (C_D)

Flight Velocity (V) (m/s)

5 m/s (~10 kts) 200 m/s (~390 kts)

Aircraft Mass (M) (kg)

0.5 kg (Micro UAV) 1,000 kg (Light Sport)

Flight Altitude (H) (meters)

0m (Sea Level) 10,000m (~33,000 ft)

Aspect Ratio (AR)

Recommended Airfoil 98% Match

Optimized for Lift

NACA 2412

The workhorse of general aviation, famously used on the Cessna 172. Offers highly predictable stall characteristics, reasonable lift, and a good balance of speed and structural thickness.

THICKNESS: 12%

CAMBER: 2%

OPT CL: 0.2 - 0.8

Airfoil Compatibility Rankings

Analyzed 12 default aero profiles.

Wing Parameter Calculations

Required Wing Area

1.62 m²

Suggested Wingspan

3.60 m

Suggested Chord

0.45 m

Wing Thickness

5.40 cm

Estimated Lift

637.4 N

Estimated Drag

15.9 N

Reynolds Number

920,000

Aero Efficiency (L/D)

40.0

FLIGHT POWER REQUIRED: 556.5 W (0.75 HP)

AIR DENSITY (ρ): 1.058 kg/m³

Airfoil Profile Plotter

Structural Spars Chord Line Thickness Vector

SCALE: 1.0 px = 1.0 mm

Lift Coefficient (C_L) vs Alpha (α)

REQD AOI: 3.5°

Drag Polar Curve (C_L vs C_D)

EST CD: 0.015