Maximum payload for a flight time

The most payload a multirotor can carry and still hover for a target time, from its mass, rotors, battery energy, and air density by momentum theory.

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Experimental: not yet fully verified. How results are checked

Computing your own values needs JavaScript and WebAssembly. The worked example below was computed when this page was built, and the documentation under "How we got this" applies.

0.381kg

It can carry about 0.381 kg more and still hover for the target time.

Maximum takeoff mass
Hover time with no payload

Provenance

Computed by: drone.power.max-payload 1.0.0, core 0.1.0
Model: Solve (m·g0)^1.5 / √(2ρA) / (FM·η) + avionics = usable energy / target time for m
Accuracy: Momentum-theory estimate; it ignores the motors' thrust limit, so check the maximum takeoff mass in the manual.
Notes: 1 shown with the answer
Cites: Leishman, J. G., Cambridge University Press, Principles of Helicopter Aerodynamics

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Takeoff mass Everything on board, like 1.4 kg · plain numbers mean kg Rotors Like 4 Rotor diameter Like 9.4 in · plain numbers mean in Usable energy After reserve, like 72 Wh · plain numbers mean Wh Target hover time Like 20 min · plain numbers mean min

More options 6

Figure of meritoptional Rotor efficiency vs ideal, 0.4 to 0.8, default 0.6 Motor and speed-controller efficiencyoptional 0.5 to 1, default 0.85 Avionics and payload poweroptional Like 10 W; default 0 · plain numbers mean W Altitudeoptional Pressure altitude of the site, like 5000 ft; default sea level · plain numbers mean ft Air temperatureoptional Like 30 °C; default ISA for the altitude · plain numbers mean °C Density altitudeoptional Instead of altitude and temperature, like 8000 ft · plain numbers mean ft

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How we got thisFormula, worked example, sources, and proof

Model: Solve (m·g0)^1.5 / √(2ρA) / (FM·η) + avionics = usable energy / target time for m

Accuracy: Momentum-theory estimate; it ignores the motors' thrust limit, so check the maximum takeoff mass in the manual.

Worked example: The 1.4 kg quad, 72 Wh usable, 20 minutes. Source: Momentum theory (Leishman 2006, chapter 2) solved for mass. It is golden test vector v001, and every build checks the tool still gives its answer within its tolerance.

You enter

Takeoff mass: 1.4 kg
Rotor diameter: 9.4 in
Rotors: 4
Target hover time: 20 min
Usable energy: 72 Wh

You get

Maximum payload: 0.381 kg
Maximum takeoff mass: 1.781 kg
Hover time with no payload: 28.7 min

Review: Not yet independently reviewed by a Part 107 remote pilot.

Last verified: 2026-09-18, when a maintainer last confirmed this tool's sources at the issuer. See the sources ledger.

Status: version 1.0.0, core 0.1.0. See this tool in the verification report.

Checked against: 5 golden test vectors (download the test vectors, each with its source and tolerance). See how results are checked and every source.

Sources

Principles of Helicopter Aerodynamics, Leishman, J. G., Cambridge University Press, 2nd edition. Chapter 2 (momentum theory: ideal hover power T^1.5/√(2ρA), figure of merit).

Experimental means this tool has not yet met the stable bar: at least 20 golden vectors, differential tests, and an independent worked example.

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Sources

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