Breguet Range Calculator

↳

⤿

Aircraft Performance

Aircraft Design

Introduction and Governing Equations

Static Stability and Control

⤿

⤿

Propeller-Driven Airplane

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

⎘ Copy

👎

Formula

✖

Breguet Range

Formula

`"R" = ("LD"*"V"*ln("w"_{"i"}/"w"_{"f"}))/("[g]"*"c"_{"t"})`

Example

`"3752.992m"=("2.5"*"60m/s"*ln("200kg"/"100kg"))/("[g]"*"10.17kg/h/N")`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF

Breguet Range Solution

STEP 0: Pre-Calculation Summary

Formula Used

Range of aircraft = (Lift-to-drag ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)
R = (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 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.
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: 60 Meter per Second --> 60 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 = (LD*V*ln(w_i/w_f))/([g]*c_t) --> (2.5*60*ln(200/100))/([g]*0.002825)

Evaluating ... ...

R = 3752.99159998362

STEP 3: Convert Result to Output's Unit

3752.99159998362 Meter --> No Conversion Required

FINAL ANSWER

3752.99159998362 ≈ 3752.992 Meter <-- Range of aircraft

(Calculation completed in 00.020 seconds)

You are here -

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

Credits

Created by Shreyash

Rajiv Gandhi Institute of Technology (RGIT), Mumbai

Shreyash has created this Calculator and 10+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< 18 Jet Airplane Calculators

Thrust-Specific Fuel Consumption for given Range of Jet Airplane

Go Thrust-Specific Fuel Consumption = (sqrt(8/(Freestream density*Reference Area)))*(1/(Range of aircraft*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel)))

Range of Jet Airplane

Go Range of aircraft = (sqrt(8/(Freestream density*Reference Area)))*(1/(Thrust-Specific Fuel Consumption*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel)))

Maximum Lift to Drag Ratio given Range for Jet Aircraft

Go Maximum Lift to Drag Ratio = (Range of aircraft*Specific Fuel Consumption)/(Velocity at Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))

Specific Fuel Consumption given Range for Jet Aircraft

Go Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft

Breguet Range

Go Range of aircraft = (Lift-to-drag ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)

Breguet Endurance Equation

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

Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

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

Endurance of Jet Airplane

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

Cruise Weight Fraction for Jet Aircraft

Go Cruise Weight Fraction = exp((Range of aircraft*Specific Fuel Consumption*(-1))/(0.866*1.32*Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio))

Constant Speed Cruise using Range Equation

Go Range of aircraft = Flight Velocity/(Thrust-Specific Fuel Consumption*Total Thrust)*int(1,x,Weight without fuel,Gross Weight)

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane

Go Lift-to-drag ratio = Specific Fuel Consumption*Range of aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without fuel))

Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft

Go Maximum Lift to Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)

Specific Fuel Consumption given Preliminary Endurance for Jet Aircraft

Go Specific Fuel Consumption = (Maximum Lift to Drag Ratio*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/Endurance of Aircraft

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

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

Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*Lift-to-drag ratio*ln(Gross Weight/Weight without fuel)

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

Go Lift-to-drag ratio = Thrust-Specific Fuel Consumption*Endurance of Aircraft/(ln(Gross Weight/Weight without fuel))

Loiter Weight Fraction for Jet Aircraft

Go Loiter weight Fraction for Jet aircraft = exp(((-1)*Endurance of Aircraft*Specific Fuel Consumption)/Maximum Lift to Drag Ratio)

Average Value Range Equation

Go Average Value Range Equation = Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity))

Breguet Range Formula

Range of aircraft = (Lift-to-drag ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)
R = (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 aircraft = (Lift-to-drag ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption) to calculate the Range of aircraft, The Breguet Range Equation provides us with the range of the aircraft by knowing characteristics such as the L/D ratio, aircraft velocity, specific fuel consumption, and aircraft's initial and final weight. It is sort of an equivalent mission analysis tool for typical aircraft using liquid fuel. Range of aircraft is denoted by R 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 -> 12722.64 = (2.5*60*ln(200/100))/([g]*0.002825).

FAQ

What is Breguet Range?

The Breguet Range Equation provides us with the range of the aircraft by knowing characteristics such as the L/D ratio, aircraft velocity, specific fuel consumption, and aircraft's initial and final weight. It is sort of an equivalent mission analysis tool for typical aircraft using liquid fuel and is represented as R = (LD*V*ln(w_i/w_f))/([g]*c_t) or Range of 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?

The Breguet Range Equation provides us with the range of the aircraft by knowing characteristics such as the L/D ratio, aircraft velocity, specific fuel consumption, and aircraft's initial and final weight. It is sort of an equivalent mission analysis tool for typical aircraft using liquid fuel is calculated using Range of 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 aircraft?

In this formula, Range of 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 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 aircraft = Flight Velocity/(Thrust-Specific Fuel Consumption*Total Thrust)*int(1,x,Weight without fuel,Gross Weight)

Home

FREE PDFs

🔍 Search