Specific Fuel Consumption given Range for Prop-Driven Aircraft Calculator

✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+10% -10%
✖The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.ⓘ Maximum Lift-to-Drag Ratio [LDmax_ratio]			+10% -10%
✖Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.ⓘ Weight at Start of Cruise Phase [W_i]			+10% -10%
✖Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.ⓘ Weight at End of Cruise Phase [W_f]			+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%

✖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 given Range for Prop-Driven Aircraft [c]

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Specific Fuel Consumption given Range for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

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
c = (η*LDmax_ratio*ln(W_i/W_f))/R_prop
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).
Maximum Lift-to-Drag Ratio - The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.
Weight at Start of Cruise Phase - (Measured in Kilogram) - Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.
Weight at End of Cruise Phase - (Measured in Kilogram) - Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.
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.

STEP 1: Convert Input(s) to Base Unit

Propeller Efficiency: 0.93 --> No Conversion Required
Maximum Lift-to-Drag Ratio: 5.081527 --> No Conversion Required
Weight at Start of Cruise Phase: 450 Kilogram --> 450 Kilogram No Conversion Required
Weight at End of Cruise Phase: 350 Kilogram --> 350 Kilogram No Conversion Required
Range of Propeller Aircraft: 7126.017 Meter --> 7126.017 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c = (η*LDmax_ratio*ln(W_i/W_f))/R_prop --> (0.93*5.081527*ln(450/350))/7126.017

Evaluating ... ...

c = 0.000166666284840895

STEP 3: Convert Result to Output's Unit

0.000166666284840895 Kilogram per Second per Watt -->0.599998625427222 Kilogram per Hour per Watt (Check conversion here)

FINAL ANSWER

0.599998625427222 ≈ 0.599999 Kilogram per Hour per Watt <-- Specific Fuel Consumption

(Calculation completed in 00.020 seconds)

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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 given Range for Prop-Driven Aircraft Formula

LaTeX Go

What is Specific Fuel Consumption?

The Specific Fuel Consumption (SFC) is a technical figure of merit for an engine that indicates how efficiently the engine is burning fuel and converting it to thrust. SFC depends on the type and design technology of the engine and also the type of fuel. SFC is used to describe the fuel efficiency of an engine with respect to its mechanical output.

How to Calculate Specific Fuel Consumption given Range for Prop-Driven Aircraft?

Specific Fuel Consumption given Range for Prop-Driven Aircraft calculator uses 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 to calculate the Specific Fuel Consumption, Specific Fuel Consumption given Range for Prop-Driven Aircraft is a measure of the amount of fuel consumed by a propeller-driven aircraft in relation to its range, taking into account the propeller efficiency, lift-to-drag ratio, and the change in aircraft weight during cruise, this formula provides a crucial estimate of the fuel efficiency of an aircraft, helping aircraft designers and engineers optimize their designs for better performance and reduced fuel consumption. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption given Range for Prop-Driven Aircraft using this online calculator? To use this online calculator for Specific Fuel Consumption given Range for Prop-Driven Aircraft, enter Propeller Efficiency (η), Maximum Lift-to-Drag Ratio (LDmax_ratio), Weight at Start of Cruise Phase (W_i), Weight at End of Cruise Phase (W_f) & Range of Propeller Aircraft (R_prop) and hit the calculate button. Here is how the Specific Fuel Consumption given Range for Prop-Driven Aircraft calculation can be explained with given input values -> 2159.771 = (0.93*5.081527*ln(450/350))/7126.017.

FAQ

What is Specific Fuel Consumption given Range for Prop-Driven Aircraft?

Specific Fuel Consumption given Range for Prop-Driven Aircraft is a measure of the amount of fuel consumed by a propeller-driven aircraft in relation to its range, taking into account the propeller efficiency, lift-to-drag ratio, and the change in aircraft weight during cruise, this formula provides a crucial estimate of the fuel efficiency of an aircraft, helping aircraft designers and engineers optimize their designs for better performance and reduced fuel consumption and is represented as c = (η*LDmax_ratio*ln(W_i/W_f))/R_prop or 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. Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve, Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission, Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan & Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.

How to calculate Specific Fuel Consumption given Range for Prop-Driven Aircraft?

Specific Fuel Consumption given Range for Prop-Driven Aircraft is a measure of the amount of fuel consumed by a propeller-driven aircraft in relation to its range, taking into account the propeller efficiency, lift-to-drag ratio, and the change in aircraft weight during cruise, this formula provides a crucial estimate of the fuel efficiency of an aircraft, helping aircraft designers and engineers optimize their designs for better performance and reduced fuel consumption is calculated using 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. To calculate Specific Fuel Consumption given Range for Prop-Driven Aircraft, you need Propeller Efficiency (η), Maximum Lift-to-Drag Ratio (LDmax_ratio), Weight at Start of Cruise Phase (W_i), Weight at End of Cruise Phase (W_f) & Range of Propeller Aircraft (R_prop). With our tool, you need to enter the respective value for Propeller Efficiency, Maximum Lift-to-Drag Ratio, Weight at Start of Cruise Phase, Weight at End of Cruise Phase & Range of Propeller Aircraft 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, Maximum Lift-to-Drag Ratio, Weight at Start of Cruise Phase, Weight at End of Cruise Phase & Range of Propeller Aircraft. 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/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))

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