Rate of Climb of Aircraft Calculator

✖Power Available is a function of the propulsion system, the flight velocity, altitude, etc, is the portion of the total system power that can be used by a dispatcher to meet the system's loads.ⓘ Power Available [P_a]			+10% -10%
✖Power Required is the amount of power required to maintain the aircraft in constant altitude and speed.ⓘ Power Required [P_r]			+10% -10%
✖Aircraft Weight is the total aircraft weight at any moment during the flight or ground operation.ⓘ Aircraft Weight [W]			+10% -10%

✖The Rate of Climb (RoC) is defined as the aircraft's vertical speed – the positive or negative rate of altitude change with respect to time.ⓘ Rate of Climb of Aircraft [RC]

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Rate of Climb of Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Rate of Climb = (Power Available-Power Required)/Aircraft Weight
RC = (P_a-P_r)/W
This formula uses 4 Variables

Variables Used

Rate of Climb - (Measured in Meter per Second) - The Rate of Climb (RoC) is defined as the aircraft's vertical speed – the positive or negative rate of altitude change with respect to time.
Power Available - (Measured in Watt) - Power Available is a function of the propulsion system, the flight velocity, altitude, etc, is the portion of the total system power that can be used by a dispatcher to meet the system's loads.
Power Required - (Measured in Watt) - Power Required is the amount of power required to maintain the aircraft in constant altitude and speed.
Aircraft Weight - (Measured in Newton) - Aircraft Weight is the total aircraft weight at any moment during the flight or ground operation.

STEP 1: Convert Input(s) to Base Unit

Power Available: 38199 Watt --> 38199 Watt No Conversion Required
Power Required: 1000 Watt --> 1000 Watt No Conversion Required
Aircraft Weight: 10000 Newton --> 10000 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

RC = (P_a-P_r)/W --> (38199-1000)/10000

Evaluating ... ...

RC = 3.7199

STEP 3: Convert Result to Output's Unit

3.7199 Meter per Second --> No Conversion Required

FINAL ANSWER

3.7199 Meter per Second <-- Rate of Climb

(Calculation completed in 00.004 seconds)

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Credits

Created by Kaki Varun Krishna

Mahatma Gandhi Institute of Technology (MGIT), Hyderabad

Kaki Varun Krishna has created this Calculator and 25+ more calculators!

Verified by Abhinav Gupta

Defence institute of advanced technology (DRDO) (DIAT), pune

Abhinav Gupta has verified this Calculator and 8 more calculators!

< Climbing Flight Calculators

Flight path angle at given rate of climb

LaTeX Go Flight Path Angle = asin(Rate of Climb/Velocity)

Velocity of aircraft at given rate of climb

LaTeX Go Velocity = Rate of Climb/sin(Flight Path Angle)

Rate of Climb

LaTeX Go Rate of Climb = Velocity*sin(Flight Path Angle)

Weight of Aircraft for given Excess Power

LaTeX Go Aircraft Weight = Excess Power/Rate of Climb

Rate of Climb of Aircraft Formula

LaTeX Go

Rate of Climb = (Power Available-Power Required)/Aircraft Weight
RC = (P_a-P_r)/W

what is aircraft ceiling?

With respect to aircraft performance, a ceiling is the maximum density altitude an aircraft can reach under a set of conditions, as determined by its flight envelope.

How to Calculate Rate of Climb of Aircraft?

Rate of Climb of Aircraft calculator uses Rate of Climb = (Power Available-Power Required)/Aircraft Weight to calculate the Rate of Climb, Rate of Climb of Aircraft is a measure of how fast an aircraft is ascending or descending vertically through the air. It represents the change in altitude per unit of time and is typically expressed in feet per minute (ft/min) or meters per second (m/s). Rate of Climb is denoted by RC symbol.

How to calculate Rate of Climb of Aircraft using this online calculator? To use this online calculator for Rate of Climb of Aircraft, enter Power Available (P_a), Power Required (P_r) & Aircraft Weight (W) and hit the calculate button. Here is how the Rate of Climb of Aircraft calculation can be explained with given input values -> 3.7199 = (38199-1000)/10000.

FAQ

What is Rate of Climb of Aircraft?

Rate of Climb of Aircraft is a measure of how fast an aircraft is ascending or descending vertically through the air. It represents the change in altitude per unit of time and is typically expressed in feet per minute (ft/min) or meters per second (m/s) and is represented as RC = (P_a-P_r)/W or Rate of Climb = (Power Available-Power Required)/Aircraft Weight. Power Available is a function of the propulsion system, the flight velocity, altitude, etc, is the portion of the total system power that can be used by a dispatcher to meet the system's loads, Power Required is the amount of power required to maintain the aircraft in constant altitude and speed & Aircraft Weight is the total aircraft weight at any moment during the flight or ground operation.

How to calculate Rate of Climb of Aircraft?

Rate of Climb of Aircraft is a measure of how fast an aircraft is ascending or descending vertically through the air. It represents the change in altitude per unit of time and is typically expressed in feet per minute (ft/min) or meters per second (m/s) is calculated using Rate of Climb = (Power Available-Power Required)/Aircraft Weight. To calculate Rate of Climb of Aircraft, you need Power Available (P_a), Power Required (P_r) & Aircraft Weight (W). With our tool, you need to enter the respective value for Power Available, Power Required & Aircraft Weight and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Rate of Climb?

In this formula, Rate of Climb uses Power Available, Power Required & Aircraft Weight. We can use 2 other way(s) to calculate the same, which is/are as follows -

Rate of Climb = Velocity*sin(Flight Path Angle)
Rate of Climb = Excess Power/Aircraft Weight

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