Rate of Climb Calculator
With 1500 N of excess thrust at 40 m/s, an 1100 kg aircraft climbs at 5.56209 m/s, about 1090 ft/min.
5.56208843442506 m/s
Full answer, then cut to fewer decimals (not rounded):
- 5.56208843442506 m/s
- 5.5620884344250 m/s
- 5.562088434425 m/s
- 5.56208843442 m/s
- 5.5620884344 m/s
- 5.562088434 m/s
- 5.56208843 m/s
- 5.5620884 m/s
- 5.562088 m/s
- 5.56208 m/s
- 5.5620 m/s
- 5.562 m/s
- 5.56 m/s
- 5.5 m/s
- In feet per minute
- 1094.899298 ft/min
- Climb angle γ
- 7.993005497 °
- Excess power (T − D)V
- 60000 W
Step-by-step solution
- R/C = (T − D)V ÷ W = (3000 − 1500) × 40 ÷ 10787.315
- R/C = 5.562088434 m/s
- sin γ = (T − D) ÷ W = 0.1390522109
Rate of Climb Formula
R/C = (T − D)V / W
sin γ = (T − D)/W; excess power = (T − D)V
Worked Example
3000 N thrust and 1500 N drag at 40 m/s for an 1100 kg aircraft:
- R/C = (T − D)V ÷ W = (3000 − 1500) × 40 ÷ 10787.315
- R/C = 5.562088434 m/s
- sin γ = (T − D) ÷ W = 0.1390522109
Climb angle γ: 7.993005497 ° · Excess power (T − D)V: 60000 W
GATE tip
For a propeller aircraft use power: R/C = (ηP − DV)/W. The time to climb between altitudes is the integral of dh/(R/C), often approximated with an average rate.
More Airplane Performance Calculators
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Drag Polar Calculator
C_D = C_D0 + K C_L², K = 1/(πeAR)
(L/D)max = 1/(2√(C_D0 K)) at C_L = √(C_D0/K)
Example: C_D0 = 0.025, AR = 8, e = 0.8 at C_L = 0.5: Drag coefficient C_D = 0.037434.
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Take-off Distance Calculator
s_LO ≈ 1.44 W² / (g ρ S C_L,max T)
lift-off at 1.2 V_s; drag and rolling friction neglected (Anderson)
Example: An 1100 kg aircraft, 16.2 m², C_L,max 1.6, 3 kN thrust at sea level: Ground roll s_LO ≈ 179.381 m.
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Glide Ratio Calculator
Distance = h × L/D, tan γ = 1/(L/D)
sink rate = V sin γ
Example: Gliding from 1000 m with L/D = 12: Glide distance = 12000 m.
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Lift Equation Calculator
L = ½ ρ V² S C_L
ρ air density, V true airspeed, S wing area, C_L lift coefficient; drag uses C_D the same way
Example: A 16.2 m² wing at 60 m/s and C_L = 0.5 at sea level: Lift L = 17860.5 N.
Frequently asked questions
What are the absolute and service ceilings?
Absolute ceiling: where the maximum rate of climb falls to zero. Service ceiling: where it falls to 100 ft/min (0.5 m/s).
Best angle or best rate?
Best angle (V_x) maximises excess thrust, for clearing obstacles; best rate (V_y) maximises excess power and is faster.
Sources
- The International System of Units (SI), 9th edition (SI Brochure), Bureau International des Poids et Mesures .
Last reviewed: . Factors are stored exactly and computed with 50-digit decimal arithmetic. See how we verify conversion factors.
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APA
Scientific Converters. (2026, October 15). Rate of Climb Calculator. Retrieved October 25, 2026, from https://scientificconverters.com/calculators/rate-of-climb-calculator/
IEEE
Scientific Converters, "Rate of Climb Calculator," scientificconverters.com. Accessed: Oct. 25, 2026. [Online]. Available: https://scientificconverters.com/calculators/rate-of-climb-calculator/