Breguet Range Calculator

✖The Lift-to-Drag Ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air.ⓘ Lift-to-Drag Ratio [LD]			+10% -10%
✖Flight Velocity is the speed with which the aircraft moves through the air.ⓘ Flight Velocity [V]			+10% -10%
✖Initial Weight is the weight of the aircraft at the starting point of the flight before takeoff.ⓘ Initial Weight [w_i]			+10% -10%
✖Final Weight is the weight of the aircraft after landing at the end of the destination.ⓘ Final Weight [w_f]			+10% -10%
✖Thrust-Specific Fuel Consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output.ⓘ Thrust-Specific Fuel Consumption [c_t]			+10% -10%

✖Range of Jet Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Breguet Range [R_jet]

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Breguet Range Solution

STEP 0: Pre-Calculation Summary

Formula Used

Range of Jet Aircraft = (Lift-to-Drag Ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)
R_jet = (LD*V*ln(w_i/w_f))/([g]*c_t)
This formula uses 1 Constants, 1 Functions, 6 Variables

Constants Used

[g] - Gravitational acceleration on Earth Value Taken As 9.80665

Functions Used

ln - The natural logarithm, also known as the logarithm to the base e, is the inverse function of the natural exponential function., ln(Number)

Variables Used

Range of Jet Aircraft - (Measured in Meter) - Range of Jet Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.
Lift-to-Drag Ratio - The Lift-to-Drag Ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air.
Flight Velocity - (Measured in Meter per Second) - Flight Velocity is the speed with which the aircraft moves through the air.
Initial Weight - (Measured in Kilogram) - Initial Weight is the weight of the aircraft at the starting point of the flight before takeoff.
Final Weight - (Measured in Kilogram) - Final Weight is the weight of the aircraft after landing at the end of the destination.
Thrust-Specific Fuel Consumption - (Measured in Kilogram per Second per Newton) - Thrust-Specific Fuel Consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output.

STEP 1: Convert Input(s) to Base Unit

Lift-to-Drag Ratio: 2.5 --> No Conversion Required
Flight Velocity: 114 Meter per Second --> 114 Meter per Second No Conversion Required
Initial Weight: 200 Kilogram --> 200 Kilogram No Conversion Required
Final Weight: 100 Kilogram --> 100 Kilogram No Conversion Required
Thrust-Specific Fuel Consumption: 10.17 Kilogram per Hour per Newton --> 0.002825 Kilogram per Second per Newton (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

R_jet = (LD*V*ln(w_i/w_f))/([g]*c_t) --> (2.5*114*ln(200/100))/([g]*0.002825)

Evaluating ... ...

R_jet = 7130.68403996888

STEP 3: Convert Result to Output's Unit

7130.68403996888 Meter --> No Conversion Required

FINAL ANSWER

7130.68403996888 ≈ 7130.684 Meter <-- Range of Jet Aircraft

(Calculation completed in 00.035 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Range and Endurance » Aerospace » Jet Airplane » Breguet Range

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Created by Shreyash

Rajiv Gandhi Institute of Technology (RGIT), Mumbai

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National Institute Of Technology (NIT), Hamirpur

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< Jet Airplane Calculators

Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

LaTeX Go Thrust-Specific Fuel Consumption = Lift Coefficient*(ln(Gross Weight/Weight without Fuel))/(Drag Coefficient*Endurance of Aircraft)

Endurance of Jet Airplane

LaTeX Go Endurance of Aircraft = Lift Coefficient*(ln(Gross Weight/Weight without Fuel))/(Drag Coefficient*Thrust-Specific Fuel Consumption)

Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag Ratio of Jet Airplane

LaTeX Go Thrust-Specific Fuel Consumption = (1/Endurance of Aircraft)*Lift-to-Drag Ratio*ln(Gross Weight/Weight without Fuel)

Endurance for given Lift-to-Drag Ratio of Jet Airplane

LaTeX Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*Lift-to-Drag Ratio*ln(Gross Weight/Weight without Fuel)

Breguet Range Formula

LaTeX Go

Range of Jet Aircraft = (Lift-to-Drag Ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)
R_jet = (LD*V*ln(w_i/w_f))/([g]*c_t)

What is specific fuel consumption?

Specific fuel consumption (SFC) is the fuel efficiency of an engine design with respect to thrust output. SFC measures a power plant's efficiency in converting chemical energy into mechanical energy. It is crucial to the operation of the aircraft as well as the design of the aircraft.

L/D ratio of an aircraft

The L/D denotes the lift to drag ratio of an aircraft. It describes the aerodynamic efficiency under given flight conditions. Higher the value of L/D, the greater is the efficiency.

How to Calculate Breguet Range?

Breguet Range calculator uses Range of Jet Aircraft = (Lift-to-Drag Ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption) to calculate the Range of Jet Aircraft, Breguet Range is a measure of the maximum distance an aircraft can travel, calculated by considering factors such as lift-to-drag ratio, flight velocity, initial and final weights, and thrust-specific fuel consumption, providing a critical performance indicator for jet aircraft. Range of Jet Aircraft is denoted by R_jet symbol.

How to calculate Breguet Range using this online calculator? To use this online calculator for Breguet Range, enter Lift-to-Drag Ratio (LD), Flight Velocity (V), Initial Weight (w_i), Final Weight (w_f) & Thrust-Specific Fuel Consumption (c_t) and hit the calculate button. Here is how the Breguet Range calculation can be explained with given input values -> 7134.437 = (2.5*114*ln(200/100))/([g]*0.002825).

FAQ

What is Breguet Range?

Breguet Range is a measure of the maximum distance an aircraft can travel, calculated by considering factors such as lift-to-drag ratio, flight velocity, initial and final weights, and thrust-specific fuel consumption, providing a critical performance indicator for jet aircraft and is represented as R_jet = (LD*V*ln(w_i/w_f))/([g]*c_t) or Range of Jet Aircraft = (Lift-to-Drag Ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption). The Lift-to-Drag Ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air, Flight Velocity is the speed with which the aircraft moves through the air, Initial Weight is the weight of the aircraft at the starting point of the flight before takeoff, Final Weight is the weight of the aircraft after landing at the end of the destination & Thrust-Specific Fuel Consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output.

How to calculate Breguet Range?

Breguet Range is a measure of the maximum distance an aircraft can travel, calculated by considering factors such as lift-to-drag ratio, flight velocity, initial and final weights, and thrust-specific fuel consumption, providing a critical performance indicator for jet aircraft is calculated using Range of Jet Aircraft = (Lift-to-Drag Ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption). To calculate Breguet Range, you need Lift-to-Drag Ratio (LD), Flight Velocity (V), Initial Weight (w_i), Final Weight (w_f) & Thrust-Specific Fuel Consumption (c_t). With our tool, you need to enter the respective value for Lift-to-Drag Ratio, Flight Velocity, Initial Weight, Final Weight & Thrust-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 Jet Aircraft?

In this formula, Range of Jet Aircraft uses Lift-to-Drag Ratio, Flight Velocity, Initial Weight, Final Weight & Thrust-Specific Fuel Consumption. We can use 2 other way(s) to calculate the same, which is/are as follows -

Range of Jet Aircraft = (sqrt(8/(Freestream Density*Reference Area)))*(1/(Thrust-Specific Fuel Consumption*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without Fuel)))
Range of Jet Aircraft = Flight Velocity/(Thrust-Specific Fuel Consumption*Total Thrust)*int(1,x,Weight without Fuel,Gross Weight)

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