Specific Fuel Consumption for given Range and Lift-to-Drag Ratio 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-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%
✖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 and Lift-to-Drag Ratio of Propeller-Driven Airplane [c]

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

STEP 0: Pre-Calculation Summary

Formula Used

Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel))
c = (η/R_prop)*(LD)*(ln(W₀/W₁))
This formula uses 1 Functions, 6 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-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.
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-to-Drag Ratio: 2.5 --> 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 = (η/R_prop)*(LD)*(ln(W₀/W₁)) --> (0.93/7126.017)*(2.5)*(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 00.004 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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< Propeller Driven Airplane Calculators

Specific Fuel Consumption for given Range of Propeller-Driven Airplane

LaTeX 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

LaTeX 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

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

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

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

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

LaTeX Go

Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel))
c = (η/R_prop)*(LD)*(ln(W₀/W₁))

Is the maximum lift-to-drag ratio affected by the weight of the aircraft?

The maximum lift-to-drag ratio is independent of the weight of the aircraft, the area of the wing, or the wing loading.

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

Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane calculator uses Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel)) to calculate the Specific Fuel Consumption, Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane is a measure of the rate at which fuel is consumed by a propeller-driven airplane to achieve a specific range, taking into account the propeller's efficiency, lift-to-drag ratio, and the aircraft's weight, this formula provides a valuable calculation for optimizing fuel efficiency in aircraft design and operation. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane using this online calculator? To use this online calculator for Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane, enter Propeller Efficiency (η), Range of Propeller Aircraft (R_prop), Lift-to-Drag Ratio (LD), Gross Weight (W₀) & Weight without Fuel (W₁) and hit the calculate button. Here is how the Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane calculation can be explained with given input values -> 2160.005 = (0.93/7126.017)*(2.5)*(ln(5000/3000)).

FAQ

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

Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane is a measure of the rate at which fuel is consumed by a propeller-driven airplane to achieve a specific range, taking into account the propeller's efficiency, lift-to-drag ratio, and the aircraft's weight, this formula provides a valuable calculation for optimizing fuel efficiency in aircraft design and operation and is represented as c = (η/R_prop)*(LD)*(ln(W₀/W₁)) or Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift-to-Drag Ratio)*(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-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, 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 and Lift-to-Drag Ratio of Propeller-Driven Airplane?

Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane is a measure of the rate at which fuel is consumed by a propeller-driven airplane to achieve a specific range, taking into account the propeller's efficiency, lift-to-drag ratio, and the aircraft's weight, this formula provides a valuable calculation for optimizing fuel efficiency in aircraft design and operation is calculated using Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel)). To calculate Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane, you need Propeller Efficiency (η), Range of Propeller Aircraft (R_prop), Lift-to-Drag Ratio (LD), 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-to-Drag Ratio, 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-to-Drag Ratio, Gross Weight & Weight without Fuel. We can use 3 other way(s) to calculate the same, which is/are as follows -

Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(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

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