FROM COMPONENTS TO LIFT

Make the math
part of the design.

Explore how mass, rotor count, and thrust connect.
Change an input. Follow the physics.

Deterministic calculationsSI units inside. Every equation visible.

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Linked equations

LIVE

One connected chain. Display values rounded to at most 7 decimal places.

Total mass

m = Σ mᵢ

0.25 + 0.35 + 0.28 + 0.12 kg

1 kg

1,000 g

Every component contributes to the mass the rotors must lift.

Weight force

W = m × g

1 kg × 9.80665 m/s²

9.80665 N

Downward gravitational force

Mass is an amount of matter; weight is the force gravity exerts on it.

Hover / motor

Tₕ = W ÷ n

9.80665 N ÷ 4 rotors

2.4516625 N

250 gf per motor

In static hover, combined upward thrust balances the aircraft’s weight.

Target / motor

Tₜ = W × R ÷ n

9.80665 N × 2 ÷ 4 rotors

4.903325 N

500 gf per motor

The target ratio provides thrust capacity above the hover requirement.

Thrust requirements

Combined target thrust19.6133 N

4 motors × 4.903325 N per motor

Motor performance comparison

Optional: enter measured maximum thrust for one motor with your specific propeller, battery voltage, and test conditions.

Performance unknown

Add a measurement to assess the target. Sizing results remain available.

Force balance

Combined forces for the current design.

Solid green: hover thrust. Dashed: target capacity, not simultaneous extra force. Arrow lengths share a scale; aircraft is schematic.

Mass → motor thrust

Required thrust per motor as total mass changes.

Target (2×) Hover (1×)

At 4 rotors, each additional 100 g requires 0.4903325 N more target thrust per motor. The chart rescales around your current mass.

Model assumptions & unit conversions +

Static multirotor sizing with equal thrust across all rotors. g = 9.80665 m/s². The target thrust-to-weight ratio compares total thrust capacity with weight; it does not mean the aircraft uses maximum thrust in hover.

1 kg = 1,000 g. 1 gram-force (gf) = 0.00980665 N. N → gf: divide by 0.00980665. Mass in grams and force in gram-force are different quantities.

Motor performance depends on the motor, propeller, battery voltage, and measurement conditions you supply. This model excludes aerodynamic interactions, flight dynamics, battery discharge, and structural strength. Meeting the arithmetic target does not certify a flight-ready design.

Illustrative starting masses total 1 kg; they are not recommended component specifications. Designs are saved only in this browser, with no accounts or synchronization.