## 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)/Power 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.
Power Specific Fuel Consumption - (Measured in Kilogram per Second per Watt) - Power 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: 37.5 Kilogram --> 37.5 Kilogram No Conversion Required
Aircraft Weight: 1001 Newton --> 1001 Newton No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required
Drag Coefficient: 0.51 --> No Conversion Required
Rotor Efficiency: 3.33 --> No Conversion Required
Coefficient of Power loss: 2.3 --> No Conversion Required
Power 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/CDr*(ξ)/c --> 270*37.5/1001*1.1/0.51*3.33*(2.3)/0.000166666666666667
Evaluating ... ...
R = 1002551.71299289
STEP 3: Convert Result to Output's Unit
1002551.71299289 Meter -->1002.55171299289 Kilometer (Check conversion ​here)
1002.55171299289 1002.552 Kilometer <-- Range of Aircraft
(Calculation completed in 00.004 seconds)
You are here -
Home »

## 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!

## < 25 Preliminary Design Calculators

Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft
Velocity for Maximum Endurance = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Endurance of Aircraft)
Preliminary Endurance for Prop-Driven Aircraft
Endurance of Aircraft = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Velocity for Maximum Endurance)
Velocity for Maximizing Range given Range for Jet Aircraft
Velocity at Maximum Lift to Drag Ratio = (Range of Aircraft*Power Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase))
Optimum Range for Jet Aircraft in Cruising Phase
Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)
Optimum Range for Prop-Driven Aircraft in Cruising Phase
Optimum Range of Aircraft = (Propeller Efficiency*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)
Preliminary Endurance for Jet Aircraft
Preliminary Endurance of Aircraft = (Maximum Lift-to-Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase))/Power Specific Fuel Consumption
Maximum Lift over Drag
Maximum Lift-to-Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5)
Preliminary Take Off Weight Built-up for Manned Aircraft
Desired Takeoff Weight = Payload Carried+Operating Empty Weight+Fuel Weight to be Carried+Crew Weight
Payload Carried = Desired Takeoff Weight-Operating Empty Weight-Crew Weight-Fuel Weight to be Carried
Empty Weight given Takeoff Weight
Operating Empty Weight = Desired Takeoff Weight-Fuel Weight to be Carried-Payload Carried-Crew Weight
Crew Weight given Takeoff Weight
Crew Weight = Desired Takeoff Weight-Payload Carried-Fuel Weight to be Carried-Operating Empty Weight
Fuel Weight given Takeoff Weight
Fuel Weight to be Carried = Desired Takeoff Weight-Operating Empty Weight-Payload Carried-Crew Weight
Preliminary Take off Weight Built-Up for Manned Aircraft given Fuel and Empty Weight Fraction
Desired Takeoff Weight = (Payload Carried+Crew Weight)/(1-Fuel Fraction-Empty Weight Fraction)
Fuel Fraction given Takeoff Weight and Empty Weight Fraction
Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight
Empty Weight Fraction given Takeoff Weight and Fuel Fraction
Empty Weight Fraction = 1-Fuel Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight
Payload Weight given Fuel and Empty Weight Fractions
Payload Carried = Desired Takeoff Weight*(1-Empty Weight Fraction-Fuel Fraction)-Crew Weight
Crew Weight given Fuel and Empty Weight Fraction
Crew Weight = Desired Takeoff Weight*(1-Empty Weight Fraction-Fuel Fraction)-Payload Carried
Takeoff Weight given Empty Weight Fraction
Desired Takeoff Weight = Operating Empty Weight/Empty Weight Fraction
Empty Weight given Empty Weight Fraction
Operating Empty Weight = Empty Weight Fraction*Desired Takeoff Weight
Empty Weight Fraction
Empty Weight Fraction = Operating Empty Weight/Desired Takeoff Weight
Winglet Friction Coefficient
Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58))
Takeoff Weight given Fuel Fraction
Desired Takeoff Weight = Fuel Weight to be Carried/Fuel Fraction
Fuel Weight given Fuel Fraction
Fuel Weight to be Carried = Fuel Fraction*Desired Takeoff Weight
Fuel Fraction
Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight
Design Range given Range Increment
Design Range = Harmonic Range-Range Increment of Aircraft

## Helicopter Flying Range Formula

Range of Aircraft = 270*Weight of Fuel/Aircraft Weight*Lift Coefficient/Drag Coefficient*Rotor Efficiency*(Coefficient of Power loss)/Power 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)/Power Specific Fuel Consumption to calculate the Range of Aircraft, The Helicopter Flying Range formula refers to the maximum distance it can travel in a single flight while carrying a specified payload (including fuel, crew, passengers, and cargo), several factors influence the flying range of a helicopter, including fuel capacity, fuel consumption rate, cruising speed, altitude, weather conditions, and payload weight. 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 r), Coefficient of Power loss (ξ) & Power Specific Fuel Consumption (c) and hit the calculate button. Here is how the Helicopter Flying Range calculation can be explained with given input values -> 1.015919 = 270*37.5/1001*1.1/0.51*3.33*(2.3)/0.000166666666666667.

### FAQ

What is Helicopter Flying Range?
The Helicopter Flying Range formula refers to the maximum distance it can travel in a single flight while carrying a specified payload (including fuel, crew, passengers, and cargo), several factors influence the flying range of a helicopter, including fuel capacity, fuel consumption rate, cruising speed, altitude, weather conditions, and payload weight and is represented as R = 270*GT/Wa*CL/CDr*(ξ)/c or Range of Aircraft = 270*Weight of Fuel/Aircraft Weight*Lift Coefficient/Drag Coefficient*Rotor Efficiency*(Coefficient of Power loss)/Power 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 & Power 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 refers to the maximum distance it can travel in a single flight while carrying a specified payload (including fuel, crew, passengers, and cargo), several factors influence the flying range of a helicopter, including fuel capacity, fuel consumption rate, cruising speed, altitude, weather conditions, and payload weight is calculated using Range of Aircraft = 270*Weight of Fuel/Aircraft Weight*Lift Coefficient/Drag Coefficient*Rotor Efficiency*(Coefficient of Power loss)/Power 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 r), Coefficient of Power loss (ξ) & Power 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 & Power Specific Fuel Consumption 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 Range of Aircraft?
In this formula, Range of Aircraft uses Weight of Fuel, Aircraft Weight, Lift Coefficient, Drag Coefficient, Rotor Efficiency, Coefficient of Power loss & Power Specific Fuel Consumption. We can use 1 other way(s) to calculate the same, which is/are as follows -
• Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)
Let Others Know