Specific Fuel Consumption for given Range of Propeller-Driven Airplane Calculator

✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+10% -10%
✖Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Range of Propeller Aircraft [R_prop]			+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%
✖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 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%

✖Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.ⓘ Specific Fuel Consumption for given Range of Propeller-Driven Airplane [c]

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Formula

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Specific Fuel Consumption for given Range of Propeller-Driven Airplane

Formula

`"c" = ("η"/"R"_{"prop"})*("C"_{"L"}/"C"_{"D"})*(ln("W"_{"0"}/"W"_{"1"}))`

Example

`"0.6kg/h/W"=("0.93"/"7126.017m")*("5"/"2")*(ln("5000kg"/"3000kg"))`

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Specific Fuel Consumption for given Range of Propeller-Driven Airplane Solution

STEP 0: Pre-Calculation Summary

Formula Used

Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel))
c = (η/R_prop)*(C_L/C_D)*(ln(W₀/W₁))
This formula uses 1 Functions, 7 Variables

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

Specific Fuel Consumption - (Measured in Kilogram per Second per Watt) - Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
Range of Propeller Aircraft - (Measured in Meter) - Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.
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.
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.
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

Propeller Efficiency: 0.93 --> No Conversion Required
Range of Propeller Aircraft: 7126.017 Meter --> 7126.017 Meter No Conversion Required
Lift Coefficient: 5 --> No Conversion Required
Drag Coefficient: 2 --> 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 = (η/R_prop)*(C_L/C_D)*(ln(W₀/W₁)) --> (0.93/7126.017)*(5/2)*(ln(5000/3000))

Evaluating ... ...

c = 0.000166666677227395

STEP 3: Convert Result to Output's Unit

0.000166666677227395 Kilogram per Second per Watt -->0.600000038018621 Kilogram per Hour per Watt (Check conversion here)

FINAL ANSWER

0.600000038018621 ≈ 0.6 Kilogram per Hour per Watt <-- Specific Fuel Consumption

(Calculation completed in 00.020 seconds)

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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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< 22 Propeller-Driven Airplane Calculators

Propeller Efficiency for given Endurance of Propeller-Driven Airplane

Go Propeller Efficiency = Endurance of Aircraft/((1/Specific Fuel Consumption)*((Lift Coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream Density*Reference Area))*(((1/Weight without Fuel)^(1/2))-((1/Gross Weight)^(1/2))))

Endurance of Propeller-Driven Airplane

Go Endurance of Propeller Aircraft = Propeller Efficiency/Specific Fuel Consumption*(Lift Coefficient^1.5)/Drag Coefficient*sqrt(2*Freestream Density*Reference Area)*((1/Weight without Fuel)^(1/2)-(1/Gross Weight)^(1/2))

Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane

Go Specific Fuel Consumption = Propeller Efficiency/Endurance of Aircraft*Lift Coefficient^1.5/Drag Coefficient*sqrt(2*Freestream Density*Reference Area)*((1/Weight without Fuel)^(1/2)-(1/Gross Weight)^(1/2))

Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft

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

Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft

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

Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft

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

Specific Fuel Consumption for given Range of Propeller-Driven Airplane

Go Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel))

Range of Propeller-Driven Airplane

Go Range of Propeller Aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel))

Propeller Efficiency for given Range of Propeller-Driven Airplane

Go Propeller Efficiency = Range of Propeller Aircraft*Specific Fuel Consumption*Drag Coefficient/(Lift Coefficient*ln(Gross Weight/Weight without Fuel))

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft

Go Maximum Lift-to-Drag Ratio = (Range of Propeller Aircraft*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))

Propeller Efficiency given Range for Prop-Driven Aircraft

Go Propeller Efficiency = (Range of Propeller Aircraft*Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))

Specific Fuel Consumption given Range for Prop-Driven Aircraft

Go Specific Fuel Consumption = (Propeller Efficiency*Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of Propeller Aircraft

Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane

Go Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel))

Range of Propeller-Driven Airplane for given lift-to-drag ratio

Go Range of Propeller Aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel))

Propeller Efficiency for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane

Go Propeller Efficiency = Range of Propeller Aircraft*Specific Fuel Consumption/(Lift-to-Drag Ratio*(ln(Gross Weight/Weight without Fuel)))

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

Go Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel))

Cruise Weight Fraction for Prop-Driven Aircraft

Go Cruise Weight Fraction Propeller Aircraft = exp((Range of Propeller Aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio*Propeller Efficiency))

Propeller Efficiency for Reciprocating Engine-Propeller Combination

Go Propeller Efficiency = Available Power/Brake Power

Shaft Brake Power for Reciprocating Engine-Propeller Combination

Go Brake Power = Available Power/Propeller Efficiency

Power Available for Reciprocating Engine-Propeller Combination

Go Available Power = Propeller Efficiency*Brake Power

Lift to Drag Ratio for Maximum Endurance given Max Lift to Drag Ratio for Prop-Driven Aircraft

Go Lift to Drag Ratio at Maximum Endurance = 0.866*Maximum Lift-to-Drag Ratio

Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft

Go Maximum Lift-to-Drag Ratio = Lift to Drag Ratio at Maximum Endurance/0.866

Specific Fuel Consumption for given Range of Propeller-Driven Airplane Formula

Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel))
c = (η/R_prop)*(C_L/C_D)*(ln(W₀/W₁))

Who gave the Breguet equation?

The Breguet range equation was given by a French aircraft designer and builder, Louis Charles Breguet.

How to Calculate Specific Fuel Consumption for given Range of Propeller-Driven Airplane?

Specific Fuel Consumption for given Range of Propeller-Driven Airplane calculator uses Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel)) to calculate the Specific Fuel Consumption, Specific Fuel Consumption for given Range of Propeller-Driven Airplane is a measure of the amount of fuel consumed by an aircraft in relation to its weight and range, considering factors such as propeller efficiency, lift coefficient, and drag coefficient, to optimize flight performance and fuel efficiency. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption for given Range of Propeller-Driven Airplane using this online calculator? To use this online calculator for Specific Fuel Consumption for given Range of Propeller-Driven Airplane, enter Propeller Efficiency (η), Range of Propeller Aircraft (R_prop), Lift Coefficient (C_L), Drag Coefficient (C_D), Gross Weight (W₀) & Weight without Fuel (W₁) and hit the calculate button. Here is how the Specific Fuel Consumption for given Range of Propeller-Driven Airplane calculation can be explained with given input values -> 2160.005 = (0.93/7126.017)*(5/2)*(ln(5000/3000)).

FAQ

What is Specific Fuel Consumption for given Range of Propeller-Driven Airplane?

Specific Fuel Consumption for given Range of Propeller-Driven Airplane is a measure of the amount of fuel consumed by an aircraft in relation to its weight and range, considering factors such as propeller efficiency, lift coefficient, and drag coefficient, to optimize flight performance and fuel efficiency and is represented as c = (η/R_prop)*(C_L/C_D)*(ln(W₀/W₁)) or Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel)). Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, 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, 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 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 Specific Fuel Consumption for given Range of Propeller-Driven Airplane?

Specific Fuel Consumption for given Range of Propeller-Driven Airplane is a measure of the amount of fuel consumed by an aircraft in relation to its weight and range, considering factors such as propeller efficiency, lift coefficient, and drag coefficient, to optimize flight performance and fuel efficiency is calculated using Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel)). To calculate Specific Fuel Consumption for given Range of Propeller-Driven Airplane, you need Propeller Efficiency (η), Range of Propeller Aircraft (R_prop), Lift Coefficient (C_L), Drag Coefficient (C_D), Gross Weight (W₀) & Weight without Fuel (W₁). With our tool, you need to enter the respective value for Propeller Efficiency, Range of Propeller Aircraft, Lift Coefficient, Drag 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 Specific Fuel Consumption?

In this formula, Specific Fuel Consumption uses Propeller Efficiency, Range of Propeller Aircraft, Lift Coefficient, Drag Coefficient, Gross Weight & Weight without Fuel. We can use 4 other way(s) to calculate the same, which is/are as follows -

Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel))
Specific Fuel Consumption = Propeller Efficiency/Endurance of Aircraft*Lift Coefficient^1.5/Drag Coefficient*sqrt(2*Freestream Density*Reference Area)*((1/Weight without Fuel)^(1/2)-(1/Gross Weight)^(1/2))
Specific Fuel Consumption = (Propeller Efficiency*Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of Propeller Aircraft
Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance Prop*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance)

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