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Aircraft Wing Loading Calculator — result sheet
Calculate aircraft wing loading from mass, gravity, and projected wing planform area, with optional customary-unit output.
Inputs used
Results
Visual chart
Breakdown
Calculation steps
Returned data table
Formula and methodology
Formula: Wing loading = weight/wing area = mass × gravity / projected planform area.
Wing loading is the aircraft weight carried per unit projected wing planform area. It is a useful comparison quantity, but it is not a stall-speed prediction without lift coefficient, air density, configuration, and flight-condition inputs.
This result follows the calculator's declared inputs, precision, validation boundaries, and model limits.
Input contract
- Aircraft mass — kg; minimum 1.0E-6; maximum 1000000000
- Gravitational acceleration — m/s²; minimum 1.0E-6; maximum 1000
- Projected wing planform area — m²; minimum 1.0E-6; maximum 1000000
Worked example
| Input | Value |
|---|---|
| Aircraft mass | 1200 |
| Gravitational acceleration | 9.80665 |
| Projected wing planform area | 16 |
Wing loading ≈ 735.50 N/m² = 75.00 kgf/m² = 15.36 lbf/ft².
Assumptions and limits
- Mass and area use SI units and the supplied gravity is appropriate for the calculation.
- The area is the projected planform area of the lifting wing, not total upper-and-lower surface area.
- Lift coefficient, air density, angle of attack, induced drag, loading factor, and stall behavior are not modeled.
Calculator note
Source and methodology
Use the official WorldCalculate methodology policy for the source, formula, precision, and boundary standards behind this calculator.
Planning estimate, not financial, medical, legal, or professional advice. © WorldCalculate — reuse with attribution. Built and curated by Hassan ALRowaie.
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