Range of Jet Airplane Calculator

✖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 Jet 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_jet]

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Range of Jet Airplane Solution

STEP 0: Pre-Calculation Summary

Formula Used

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)))
R_jet = (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 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.
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: 5.11 Square Meter --> 5.11 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_jet = (sqrt(8/(ρ_∞*S)))*(1/(c_t*C_D))*(sqrt(C_L))*((sqrt(W₀))-(sqrt(W₁))) --> (sqrt(8/(1.225*5.11)))*(1/(0.002825*2))*(sqrt(5))*((sqrt(5000))-(sqrt(3000)))

Evaluating ... ...

R_jet = 7130.96631373161

STEP 3: Convert Result to Output's Unit

7130.96631373161 Meter --> No Conversion Required

FINAL ANSWER

7130.96631373161 ≈ 7130.966 Meter <-- Range of Jet Aircraft

(Calculation completed in 00.004 seconds)

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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!

< 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)

Range of Jet Airplane Formula

LaTeX Go

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 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))) to calculate the Range of Jet Aircraft, Range of Jet Airplane is a calculation of the maximum distance a jet aircraft can travel, taking into account factors such as freestream density, reference area, thrust-specific fuel consumption, drag coefficient, lift coefficient, gross weight, and weight without fuel, to determine the aircraft's range. Range of Jet Aircraft is denoted by R_jet 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 -> 7130.966 = (sqrt(8/(1.225*5.11)))*(1/(0.002825*2))*(sqrt(5))*((sqrt(5000))-(sqrt(3000))).

FAQ

What is Range of Jet Airplane?

Range of Jet Airplane is a calculation of the maximum distance a jet aircraft can travel, taking into account factors such as freestream density, reference area, thrust-specific fuel consumption, drag coefficient, lift coefficient, gross weight, and weight without fuel, to determine the aircraft's range and is represented as R_jet = (sqrt(8/(ρ_∞*S)))*(1/(c_t*C_D))*(sqrt(C_L))*((sqrt(W₀))-(sqrt(W₁))) or 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))). 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?

Range of Jet Airplane is a calculation of the maximum distance a jet aircraft can travel, taking into account factors such as freestream density, reference area, thrust-specific fuel consumption, drag coefficient, lift coefficient, gross weight, and weight without fuel, to determine the aircraft's range is calculated using 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))). 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 Jet Aircraft?

In this formula, Range of Jet 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 Jet Aircraft = (Lift-to-Drag Ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)
Range of Jet Aircraft = Flight Velocity/(Thrust-Specific Fuel Consumption*Total Thrust)*int(1,x,Weight without Fuel,Gross Weight)

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