Rate of Climb for given excess power Solution

STEP 0: Pre-Calculation Summary
Formula Used
Rate of Climb = Excess Power/Aircraft weight
RC = Pexcess/W
This formula uses 3 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.
Excess Power - (Measured in Watt) - Excess Power is defined as the difference between the power available and the power required at a particular speed and altitude of aircraft.
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
Excess Power: 37197.6 Watt --> 37197.6 Watt No Conversion Required
Aircraft weight: 10000 Newton --> 10000 Newton No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
RC = Pexcess/W --> 37197.6/10000
Evaluating ... ...
RC = 3.71976
STEP 3: Convert Result to Output's Unit
3.71976 Meter per Second --> No Conversion Required
FINAL ANSWER
3.71976 Meter per Second <-- Rate of Climb
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
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Verified by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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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 for given excess power Formula

Rate of Climb = Excess Power/Aircraft weight
RC = Pexcess/W

What is the best angle of climb speed?

The best angle of climb speed of an aircraft gets you the greatest altitude per unit of ground distance (feet per mile).

How to Calculate Rate of Climb for given excess power?

Rate of Climb for given excess power calculator uses Rate of Climb = Excess Power/Aircraft weight to calculate the Rate of Climb, The Rate of Climb for given excess power of an aircraft is defined as the ratio of excess power and weight of the aircraft. Rate of Climb is denoted by RC symbol.

How to calculate Rate of Climb for given excess power using this online calculator? To use this online calculator for Rate of Climb for given excess power, enter Excess Power (Pexcess) & Aircraft weight (W) and hit the calculate button. Here is how the Rate of Climb for given excess power calculation can be explained with given input values -> 3.71976 = 37197.6/10000.

FAQ

What is Rate of Climb for given excess power?
The Rate of Climb for given excess power of an aircraft is defined as the ratio of excess power and weight of the aircraft and is represented as RC = Pexcess/W or Rate of Climb = Excess Power/Aircraft weight. Excess Power is defined as the difference between the power available and the power required at a particular speed and altitude of aircraft & Aircraft weight is the total aircraft weight at any moment during the flight or ground operation.
How to calculate Rate of Climb for given excess power?
The Rate of Climb for given excess power of an aircraft is defined as the ratio of excess power and weight of the aircraft is calculated using Rate of Climb = Excess Power/Aircraft weight. To calculate Rate of Climb for given excess power, you need Excess Power (Pexcess) & Aircraft weight (W). With our tool, you need to enter the respective value for Excess Power & 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 Excess Power & 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 = (Power Available-Power Required)/Aircraft weight
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