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Helicopter Flying range Calculator

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✖Weight of Fuel is the weight of the fuel present in the aircraft before takeoff.ⓘ Weight of Fuel [GT]
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✖Aircraft weight is the total aircraft weight at any moment during the flight or ground operation.ⓘ Aircraft Weight [Wa]
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✖The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.ⓘ Lift Coefficient [CL]
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✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [CD]
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✖Rotor efficiency is defined as the ratio of the output to that of input, Rotor efficiency of the three phase induction motor.ⓘ Rotor efficiency [ηr]
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✖Coefficient of Power loss takes place in the transmission of power between the rotors and shafts due to cooling.ⓘ Coefficient of Power loss [ξ]
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✖Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.ⓘ Specific Fuel Consumption [c]
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✖Range of aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Helicopter Flying range [R]
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Helicopter Flying range

Formula
`"R" = 270*("G"_{"T"}/"W"_{"a"}) *("C"_{"L"}/"C"_{"D"})*("η"_{"r"}*("ξ")/"c")`

Example
`"8.2E^6m"=270*("18000kg"/"1000N") *("1.1"/"30")*("3.33"*("2.3")/"0.6kg/h/W")`

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Helicopter Flying range Solution

STEP 0: Pre-Calculation Summary
Formula Used
Range of Aircraft = 270*(Weight of Fuel/Aircraft Weight) *(Lift Coefficient/Drag Coefficient)*(Rotor efficiency*(Coefficient of Power loss)/Specific Fuel Consumption)
R = 270*(GT/Wa) *(CL/CD)*(ηr*(ξ)/c)
This formula uses 8 Variables
Variables Used
Range of Aircraft - (Measured in Meter) - Range of aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.
Weight of Fuel - (Measured in Kilogram) - Weight of Fuel is the weight of the fuel present in the aircraft before takeoff.
Aircraft Weight - (Measured in Newton) - Aircraft weight is the total aircraft weight at any moment during the flight or ground operation.
Lift Coefficient - The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
Rotor efficiency - Rotor efficiency is defined as the ratio of the output to that of input, Rotor efficiency of the three phase induction motor.
Coefficient of Power loss - Coefficient of Power loss takes place in the transmission of power between the rotors and shafts due to cooling.
Specific Fuel Consumption - (Measured in Kilogram per Second per Watt) - Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.
STEP 1: Convert Input(s) to Base Unit
Weight of Fuel: 18000 Kilogram --> 18000 Kilogram No Conversion Required
Aircraft Weight: 1000 Newton --> 1000 Newton No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required
Drag Coefficient: 30 --> No Conversion Required
Rotor efficiency: 3.33 --> No Conversion Required
Coefficient of Power loss: 2.3 --> No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
STEP 2: Evaluate Formula
Substituting Input Values in Formula
R = 270*(GT/Wa) *(CL/CD)*(ηr*(ξ)/c) --> 270*(18000/1000) *(1.1/30)*(3.33*(2.3)/0.000166666666666667)
Evaluating ... ...
R = 8189002.79999998
STEP 3: Convert Result to Output's Unit
8189002.79999998 Meter --> No Conversion Required
FINAL ANSWER
8189002.79999998 ≈ 8.2E+6 Meter <-- Range of Aircraft
(Calculation completed in 00.005 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
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10+ Parameters Calculators

Helicopter Flying range
Go Range of Aircraft = 270*(Weight of Fuel/Aircraft Weight) *(Lift Coefficient/Drag Coefficient)*(Rotor efficiency*(Coefficient of Power loss)/Specific Fuel Consumption)
Depth of missile penetration into concrete element of infinite thickness (meters)
Go Missile depth of penetration = 12*Penetration Coefficient Concrete*(Missile Wt./Frontal area of missile)*log10(1+((Missile striking velocity)^2/215000))
Weight of Glider
Go Weight = Lift Force*cos(Glide Angle)+Drag Force*sin(Glide Angle)
Maximum Blade Efficiency
Go Maximum Blade efficiency = (2*(Blade Lift Force/Blade Drag Force)-1)/(2*(Blade Lift Force/Blade Drag Force)+1)
Orbital Period
Go Orbital period = 2*pi*(Radius of Orbit^(3/2))/sqrt([G.]*Central body Mass)
Tsiolkovsky Rocket Equation
Go Change in Rocket Velocity = Specific Impulse*[g]*ln(Wet mass/Dry mass)
Modern Lift Equation
Go Lift on Airfoil = (Lift Coefficient* Air Density* Aircraft Gross Wing Area* Fluid Velocity)/2
Disk Loading
Go Load = Aircraft Weight/((pi*Diameter of Rotor)/4)
Rocket Mass Ratio
Go Rocket Mass ratio = e^(Change in Rocket Velocity/Rocket Exhaust Velocity)
Average Blade Lift Coefficient
Go Blade lift coefficient = 6*(Thrust Coefficient/Rotor Solidity)

Helicopter Flying range Formula

Range of Aircraft = 270*(Weight of Fuel/Aircraft Weight) *(Lift Coefficient/Drag Coefficient)*(Rotor efficiency*(Coefficient of Power loss)/Specific Fuel Consumption)
R = 270*(GT/Wa) *(CL/CD)*(ηr*(ξ)/c)

Difference between Endurance and range?

Endurance is the measure of how long any aerial vehicle can stay aloft, it is a measure of time (hours, minutes, seconds). Range is how far an aerial vehicle can get on a load of fuel, it is a measure of distance (miles, kilometers, yards and meters).

How to Calculate Helicopter Flying range?

Helicopter Flying range calculator uses Range of Aircraft = 270*(Weight of Fuel/Aircraft Weight) *(Lift Coefficient/Drag Coefficient)*(Rotor efficiency*(Coefficient of Power loss)/Specific Fuel Consumption) to calculate the Range of Aircraft, The Helicopter Flying range formula is defined as the distance traversed by the helicopter with constant fuel consumption rate with optimum lift and least drag. Range of Aircraft is denoted by R symbol.

How to calculate Helicopter Flying range using this online calculator? To use this online calculator for Helicopter Flying range, enter Weight of Fuel (GT), Aircraft Weight (Wa), Lift Coefficient (CL), Drag Coefficient (CD), Rotor efficiency (ηr), Coefficient of Power loss (ξ) & Specific Fuel Consumption (c) and hit the calculate button. Here is how the Helicopter Flying range calculation can be explained with given input values -> 8189.003 = 270*(18000/1000) *(1.1/30)*(3.33*(2.3)/0.000166666666666667).

FAQ

What is Helicopter Flying range?
The Helicopter Flying range formula is defined as the distance traversed by the helicopter with constant fuel consumption rate with optimum lift and least drag and is represented as R = 270*(GT/Wa) *(CL/CD)*(ηr*(ξ)/c) or Range of Aircraft = 270*(Weight of Fuel/Aircraft Weight) *(Lift Coefficient/Drag Coefficient)*(Rotor efficiency*(Coefficient of Power loss)/Specific Fuel Consumption). Weight of Fuel is the weight of the fuel present in the aircraft before takeoff, Aircraft weight is the total aircraft weight at any moment during the flight or ground operation, The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area, Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water, Rotor efficiency is defined as the ratio of the output to that of input, Rotor efficiency of the three phase induction motor, Coefficient of Power loss takes place in the transmission of power between the rotors and shafts due to cooling & Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.
How to calculate Helicopter Flying range?
The Helicopter Flying range formula is defined as the distance traversed by the helicopter with constant fuel consumption rate with optimum lift and least drag is calculated using Range of Aircraft = 270*(Weight of Fuel/Aircraft Weight) *(Lift Coefficient/Drag Coefficient)*(Rotor efficiency*(Coefficient of Power loss)/Specific Fuel Consumption). To calculate Helicopter Flying range, you need Weight of Fuel (GT), Aircraft Weight (Wa), Lift Coefficient (CL), Drag Coefficient (CD), Rotor efficiency (ηr), Coefficient of Power loss (ξ) & Specific Fuel Consumption (c). With our tool, you need to enter the respective value for Weight of Fuel, Aircraft Weight, Lift Coefficient, Drag Coefficient, Rotor efficiency, Coefficient of Power loss & Specific Fuel Consumption and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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