Range of Jet Airplane Calculator

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Propeller-Driven Airplane

✖Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream density [ρ_∞]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+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%
✖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 [C_D]			+10% -10%
✖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 [C_L]			+10% -10%
✖The Gross Weight of the airplane is the weight with full fuel and payload.ⓘ Gross Weight [W₀]			+10% -10%
✖Weight without fuel is the total weight of the airplane without fuel.ⓘ Weight without fuel [W₁]			+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.ⓘ Range of Jet Airplane [R]

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Range of Jet Airplane

Formula

`"R" = (sqrt(8/("ρ"_{"∞"}*"S")))*(1/("c"_{"t"}*"C"_{"D"}))*(sqrt("C"_{"L"}))*((sqrt("W"_{"0"}))-(sqrt("W"_{"1"})))`

Example

`"7151.991m"=(sqrt(8/("1.225kg/m³"*"5.08m²")))*(1/("10.17kg/h/N"*"2"))*(sqrt("5"))*((sqrt("5000kg"))-(sqrt("3000kg")))`

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Range of Jet Airplane Solution

STEP 0: Pre-Calculation Summary

Formula Used

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)))
R = (sqrt(8/(ρ_∞*S)))*(1/(c_t*C_D))*(sqrt(C_L))*((sqrt(W₀))-(sqrt(W₁)))
This formula uses 1 Functions, 8 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(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.
Freestream density - (Measured in Kilogram per Cubic Meter) - Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
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.
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.
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.
Gross Weight - (Measured in Kilogram) - The Gross Weight of the airplane is the weight with full fuel and payload.
Weight without fuel - (Measured in Kilogram) - Weight without fuel is the total weight of the airplane without fuel.

STEP 1: Convert Input(s) to Base Unit

Freestream density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Thrust-Specific Fuel Consumption: 10.17 Kilogram per Hour per Newton --> 0.002825 Kilogram per Second per Newton (Check conversion here)
Drag Coefficient: 2 --> No Conversion Required
Lift Coefficient: 5 --> No Conversion Required
Gross Weight: 5000 Kilogram --> 5000 Kilogram No Conversion Required
Weight without fuel: 3000 Kilogram --> 3000 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

R = (sqrt(8/(ρ_∞*S)))*(1/(c_t*C_D))*(sqrt(C_L))*((sqrt(W₀))-(sqrt(W₁))) --> (sqrt(8/(1.225*5.08)))*(1/(0.002825*2))*(sqrt(5))*((sqrt(5000))-(sqrt(3000)))

Evaluating ... ...

R = 7151.99132146183

STEP 3: Convert Result to Output's Unit

7151.99132146183 Meter --> No Conversion Required

FINAL ANSWER

7151.99132146183 ≈ 7151.991 Meter <-- Range of aircraft

(Calculation completed in 00.004 seconds)

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

Credits

Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has verified this Calculator and 200+ 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))

Range of Jet Airplane Formula

What is the range of a jet fighter?

Powered by two Pratt & Whitney F119-PW-100 turbofan engines with two-dimensional thrust vectoring nozzles, a fighter can fly at a maximum altitude of 20,000m and across a maximum range of 2,963km.

How to Calculate Range of Jet Airplane?

Range of Jet Airplane calculator uses 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))) to calculate the Range of aircraft, The Range of Jet Airplane is a function of altitude, thrust-specific fuel consumption, reference area, aerodynamic coefficients of lift & drag, and fuel weight. Range of aircraft is denoted by R symbol.

How to calculate Range of Jet Airplane using this online calculator? To use this online calculator for Range of Jet Airplane, enter Freestream density (ρ_∞), Reference Area (S), Thrust-Specific Fuel Consumption (c_t), Drag Coefficient (C_D), Lift Coefficient (C_L), Gross Weight (W₀) & Weight without fuel (W₁) and hit the calculate button. Here is how the Range of Jet Airplane calculation can be explained with given input values -> 24245.25 = (sqrt(8/(1.225*5.08)))*(1/(0.002825*2))*(sqrt(5))*((sqrt(5000))-(sqrt(3000))).

FAQ

What is Range of Jet Airplane?

The Range of Jet Airplane is a function of altitude, thrust-specific fuel consumption, reference area, aerodynamic coefficients of lift & drag, and fuel weight and is represented as R = (sqrt(8/(ρ_∞*S)))*(1/(c_t*C_D))*(sqrt(C_L))*((sqrt(W₀))-(sqrt(W₁))) or 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))). Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, Thrust-specific fuel consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output, 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, 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, The Gross Weight of the airplane is the weight with full fuel and payload & Weight without fuel is the total weight of the airplane without fuel.

How to calculate Range of Jet Airplane?

The Range of Jet Airplane is a function of altitude, thrust-specific fuel consumption, reference area, aerodynamic coefficients of lift & drag, and fuel weight is calculated using 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))). To calculate Range of Jet Airplane, you need Freestream density (ρ_∞), Reference Area (S), Thrust-Specific Fuel Consumption (c_t), Drag Coefficient (C_D), Lift Coefficient (C_L), Gross Weight (W₀) & Weight without fuel (W₁). With our tool, you need to enter the respective value for Freestream density, Reference Area, Thrust-Specific Fuel Consumption, Drag Coefficient, Lift Coefficient, Gross Weight & Weight without fuel 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 Freestream density, Reference Area, Thrust-Specific Fuel Consumption, Drag Coefficient, Lift Coefficient, Gross Weight & Weight without fuel. We can use 2 other way(s) to calculate the same, which is/are as follows -

Range of aircraft = (Lift-to-drag ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)
Range of aircraft = Flight Velocity/(Thrust-Specific Fuel Consumption*Total Thrust)*int(1,x,Weight without fuel,Gross Weight)

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