Propeller Thrust Calculator
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Ideal static thrust from actuator disk theory relates power and air velocity. Real props achieve 50–70% of ideal due to losses.
T_ideal = 2 × ρ × A × v² (actuator disk approximation)A common RC approximation scales thrust with diameter^3, RPM², and inverse pitch factor. Blade count adds marginal thrust at same diameter.
T (oz) ≈ k × D³ × (RPM/1000)² / pitch_factorThrust decreases at altitude and high temperature. Sea-level density 1.225 kg/m³ is standard; reduce ~3% per 1000 ft altitude.
T_alt = T_sea level × (ρ_alt / ρ_sea level)Updated: July 2026
5-inch (127 mm) prop, 4.3 pitch, 3-blade at 25k RPM: estimated ~800–950 g static thrust per motor. Quad total ~3.2–3.8 kg — suitable for 2–2.5 kg AUW with 1.5:1 thrust ratio.
10-inch 2-blade at 10,000 RPM on 3S: ~35–40 oz thrust. For 2.5 lb (40 oz) plane, 1:1 static thrust is adequate; aerodynamic lift provides margin in flight.
At 5000 ft, air density ~86% of sea level. Recalculate thrust — same setup produces ~14% less static thrust; size up prop or increase RPM.
Thrust scales with RPM squared. The same 5-inch prop at 15k vs 30k RPM produces vastly different thrust — always include KV, voltage, and loaded RPM.
Reduced air density at elevation cuts thrust significantly. Rebalance prop size or battery voltage for high-altitude flying locations.
Matching propeller thrust to aircraft weight is fundamental for RC drones and planes. This calculator estimates static thrust from prop diameter, pitch, RPM, blade count, and air density using momentum and empirical prop models.