Thrust-Specific Fuel Consumption for given 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%
✖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 Aircraft [R_jet]			+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%

✖Thrust-Specific Fuel Consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output.ⓘ Thrust-Specific Fuel Consumption for given Range of Jet Airplane [c_t]

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Thrust-Specific Fuel Consumption for given Range of Jet Airplane Solution

STEP 0: Pre-Calculation Summary

Formula Used

Thrust-Specific Fuel Consumption = (sqrt(8/(Freestream Density*Reference Area)))*(1/(Range of Jet Aircraft*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without Fuel)))
c_t = (sqrt(8/(ρ_∞*S)))*(1/(R_jet*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

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.
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.
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.
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
Range of Jet Aircraft: 7130 Meter --> 7130 Meter No Conversion Required
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

c_t = (sqrt(8/(ρ_∞*S)))*(1/(R_jet*C_D))*(sqrt(C_L))*((sqrt(W₀))-(sqrt(W₁))) --> (sqrt(8/(1.225*5.11)))*(1/(7130*2))*(sqrt(5))*((sqrt(5000))-(sqrt(3000)))

Evaluating ... ...

c_t = 0.00282538286624008

STEP 3: Convert Result to Output's Unit

0.00282538286624008 Kilogram per Second per Newton -->10.1713783184643 Kilogram per Hour per Newton (Check conversion here)

FINAL ANSWER

10.1713783184643 ≈ 10.17138 Kilogram per Hour per Newton <-- Thrust-Specific Fuel Consumption

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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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)

Thrust-Specific Fuel Consumption for given Range of Jet Airplane Formula

LaTeX Go

What is the longest range plane?

The longest-range jetliner in service is the Airbus A350 XWB Ultra Long Range, capable of flying up to 18,000 km (9,700 nmi).

How to Calculate Thrust-Specific Fuel Consumption for given Range of Jet Airplane?

Thrust-Specific Fuel Consumption for given Range of Jet Airplane calculator uses Thrust-Specific Fuel Consumption = (sqrt(8/(Freestream Density*Reference Area)))*(1/(Range of Jet Aircraft*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without Fuel))) to calculate the Thrust-Specific Fuel Consumption, Thrust-Specific Fuel Consumption for given Range of Jet Airplane is a measure of the rate at which fuel is consumed by a jet airplane to generate a specific amount of thrust, taking into account factors such as free stream density, reference area, range of the jet aircraft, drag coefficient, lift coefficient, gross weight, and weight without fuel, this formula provides a crucial performance metric for jet airplane design and operation. Thrust-Specific Fuel Consumption is denoted by c_t symbol.

How to calculate Thrust-Specific Fuel Consumption for given Range of Jet Airplane using this online calculator? To use this online calculator for Thrust-Specific Fuel Consumption for given Range of Jet Airplane, enter Freestream Density (ρ_∞), Reference Area (S), Range of Jet Aircraft (R_jet), Drag Coefficient (C_D), Lift Coefficient (C_L), Gross Weight (W₀) & Weight without Fuel (W₁) and hit the calculate button. Here is how the Thrust-Specific Fuel Consumption for given Range of Jet Airplane calculation can be explained with given input values -> 36637.52 = (sqrt(8/(1.225*5.11)))*(1/(7130*2))*(sqrt(5))*((sqrt(5000))-(sqrt(3000))).

FAQ

What is Thrust-Specific Fuel Consumption for given Range of Jet Airplane?

Thrust-Specific Fuel Consumption for given Range of Jet Airplane is a measure of the rate at which fuel is consumed by a jet airplane to generate a specific amount of thrust, taking into account factors such as free stream density, reference area, range of the jet aircraft, drag coefficient, lift coefficient, gross weight, and weight without fuel, this formula provides a crucial performance metric for jet airplane design and operation and is represented as c_t = (sqrt(8/(ρ_∞*S)))*(1/(R_jet*C_D))*(sqrt(C_L))*((sqrt(W₀))-(sqrt(W₁))) or Thrust-Specific Fuel Consumption = (sqrt(8/(Freestream Density*Reference Area)))*(1/(Range of Jet Aircraft*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, Range of Jet Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, 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 Thrust-Specific Fuel Consumption for given Range of Jet Airplane?

Thrust-Specific Fuel Consumption for given Range of Jet Airplane is a measure of the rate at which fuel is consumed by a jet airplane to generate a specific amount of thrust, taking into account factors such as free stream density, reference area, range of the jet aircraft, drag coefficient, lift coefficient, gross weight, and weight without fuel, this formula provides a crucial performance metric for jet airplane design and operation is calculated using Thrust-Specific Fuel Consumption = (sqrt(8/(Freestream Density*Reference Area)))*(1/(Range of Jet Aircraft*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without Fuel))). To calculate Thrust-Specific Fuel Consumption for given Range of Jet Airplane, you need Freestream Density (ρ_∞), Reference Area (S), Range of Jet Aircraft (R_jet), 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, Range of Jet Aircraft, 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 Thrust-Specific Fuel Consumption?

In this formula, Thrust-Specific Fuel Consumption uses Freestream Density, Reference Area, Range of Jet Aircraft, 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 -

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

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