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]

⎘ Copy

👎

Formula

✖

Rate of Climb of Aircraft

Formula

`"RC" = ("P"_{"a"}-"P"_{"r"})/"W"`

Example

`"3.7199m/s"=("38199W"-"1000W")/"10000N"`

Calculator

LaTeX

Reset

👍

Download Climbing Flight Formulas PDF PDF Image

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)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Performance » Aerospace » Climbing Flight » Rate of Climb of Aircraft

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!

< 16 Climbing Flight Calculators

Velocity in Accelerated Flight

Go Velocity = (Radius of Curvature/Mass of Aircraft*(Lift Force+Thrust*sin(Thrust Angle)-Mass of Aircraft*[g]*cos(Flight Path Angle)))^(1/2)

Lift in Accelerated Flight

Go Lift Force = Mass of Aircraft*[g]*cos(Flight Path Angle)+Mass of Aircraft*Velocity^2/Radius of Curvature-Thrust*sin(Thrust Angle)

Thrust in Accelerated Flight

Go Thrust = (sec(Thrust Angle))*(Drag Force+(Mass of Aircraft*[g]*sin(Flight Path Angle))+(Mass of Aircraft*Acceleration))

Drag in Accelerated Flight

Go Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration

Centrifugal Force in Accelerated Flight

Go Centrifugal Force = Lift Force+Thrust*sin(Thrust Angle)-Mass of Aircraft*[g]*cos(Flight Path Angle)

Rate of Climb of Aircraft

Go Rate of Climb = (Power Available-Power Required)/Aircraft Weight

Flight path angle at given rate of climb

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

Velocity of aircraft at given rate of climb

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

Rate of Climb

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

Velocity of Aircraft for given Excess Power

Go Velocity = Excess Power/(Thrust-Drag Force)

Thrust available for given excess power

Go Thrust = Drag Force+(Excess Power/Velocity)

Total Drag for given Excess Power

Go Drag Force = Thrust-(Excess Power/Velocity)

Excess power

Go Excess Power = Velocity*(Thrust-Drag Force)

Weight of Aircraft for given Excess Power

Go Aircraft Weight = Excess Power/Rate of Climb

Excess power for given rate of climb

Go Excess Power = Rate of Climb*Aircraft Weight

Rate of Climb for given excess power

Go Rate of Climb = Excess Power/Aircraft Weight

Rate of Climb of Aircraft Formula

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

Home

FREE PDFs

🔍 Search