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Specific Fuel Consumption given Range for Prop-Driven Aircraft Formula

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

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

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Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time. Check FAQs

c = \frac{η \cdot LDmax ratio \cdot \ln (\frac{W i}{W f})}{R prop}

c - Specific Fuel Consumption?η - Propeller Efficiency?LDmax_ratio - Maximum Lift-to-Drag Ratio?W_i - Weight at Start of Cruise Phase?W_f - Weight at End of Cruise Phase?R_prop - Range of Propeller Aircraft?

Specific Fuel Consumption given Range for Prop-Driven Aircraft Example

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Here is how the Specific Fuel Consumption given Range for Prop-Driven Aircraft equation looks like with Values.

Here is how the Specific Fuel Consumption given Range for Prop-Driven Aircraft equation looks like with Units.

Here is how the Specific Fuel Consumption given Range for Prop-Driven Aircraft equation looks like.

0.6 = \frac{0.93 \cdot 5.0815 \cdot \ln (\frac{450}{350})}{7126.017}

0.6kg/h/W = \frac{0.93 \cdot 5.0815 \cdot \ln (\frac{450kg}{350kg})}{7126.017m}

0.6 = \frac{0.93 \cdot 5.0815 \cdot \ln (\frac{450}{350})}{7126.017}

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Specific Fuel Consumption given Range for Prop-Driven Aircraft Solution

Follow our step by step solution on how to calculate Specific Fuel Consumption given Range for Prop-Driven Aircraft?

FIRST Step Consider the formula

c = \frac{η \cdot LDmax ratio \cdot \ln (\frac{W i}{W f})}{R prop}

Next Step Substitute values of Variables

∴

c = \frac{0.93 \cdot 5.0815 \cdot \ln (\frac{450kg}{350kg})}{7126.017m}

Next Step Prepare to Evaluate

∴

c = \frac{0.93 \cdot 5.0815 \cdot \ln (\frac{450}{350})}{7126.017}

Next Step Evaluate

∴

c = 0.000166666284840895kg/s/W

Next Step Convert to Output's Unit

∴

c = 0.599998625427222kg/h/W

LAST Step Rounding Answer

∴

c = 0.6kg/h/W

Specific Fuel Consumption given Range for Prop-Driven Aircraft Formula Elements

Variables

Functions

Specific Fuel Consumption

Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.

Symbol: c

Measurement: Specific Fuel ConsumptionUnit: kg/h/W

Note: Value should be greater than 0.

Formulas to find Specific Fuel Consumption

Propeller Efficiency

Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).

Symbol: η

Measurement: NAUnit: Unitless

Note: Value should be less than 1.

Formulas to find Propeller Efficiency

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.

Symbol: LDmax_ratio

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Maximum Lift-to-Drag Ratio

Weight at Start of Cruise Phase

Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.

Symbol: W_i

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight at Start of Cruise Phase

Weight at End of Cruise Phase

Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

Symbol: W_f

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight at End of Cruise Phase

Range of Propeller Aircraft

Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.

Symbol: R_prop

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Range of Propeller Aircraft

The natural logarithm, also known as the logarithm to the base e, is the inverse function of the natural exponential function.

Syntax: ln(Number)

Other Formulas to find Specific Fuel Consumption

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

c = (\frac{η}{R prop}) \cdot (\frac{C L}{C D}) \cdot (\ln (\frac{W 0}{W 1}))

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

c = (\frac{η}{R prop}) \cdot (LD) \cdot (\ln (\frac{W 0}{W 1}))

Go Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane

c = \frac{η}{E} \cdot \frac{{C L}^{1.5}}{C D} \cdot \sqrt{2 \cdot ρ ∞ \cdot S} \cdot ({(\frac{1}{W 1})}^{\frac{1}{2}} - {(\frac{1}{W 0})}^{\frac{1}{2}})

Go Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft

c = \frac{LDEmax ratio prop \cdot η \cdot \ln (\frac{W L,beg}{W L,end})}{E \cdot V Emax}

Other formulas in Propeller Driven Airplane category

Go Range of Propeller-Driven Airplane

R prop = (\frac{η}{c}) \cdot (\frac{C L}{C D}) \cdot (\ln (\frac{W 0}{W 1}))

Go Propeller Efficiency for given Range of Propeller-Driven Airplane

η = R prop \cdot c \cdot \frac{C D}{C L \cdot \ln (\frac{W 0}{W 1})}

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

R prop = (\frac{η}{c}) \cdot (LD) \cdot (\ln (\frac{W 0}{W 1}))

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

η = R prop \cdot \frac{c}{LD \cdot (\ln (\frac{W 0}{W 1}))}

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

Specific Fuel Consumption given Range for Prop-Driven Aircraft evaluator 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 evaluate 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 evaluate Specific Fuel Consumption given Range for Prop-Driven Aircraft using this online evaluator? To use this online evaluator 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.

FAQs on Specific Fuel Consumption given Range for Prop-Driven Aircraft

What is the formula to find Specific Fuel Consumption given Range for Prop-Driven Aircraft?

The formula of Specific Fuel Consumption given Range for Prop-Driven Aircraft is expressed as 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. Here is an example- 2159.771 = (0.93*5.081527*ln(450/350))/7126.017.

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

With 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) we can find Specific Fuel Consumption given Range for Prop-Driven Aircraft using the formula - 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. This formula also uses Natural Logarithm (ln) function(s).

What are the other ways to Calculate Specific Fuel Consumption?

Here are the different ways to Calculate Specific Fuel Consumption-

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))

Can the Specific Fuel Consumption given Range for Prop-Driven Aircraft be negative?

No, the Specific Fuel Consumption given Range for Prop-Driven Aircraft, measured in Specific Fuel Consumption cannot be negative.

Which unit is used to measure Specific Fuel Consumption given Range for Prop-Driven Aircraft?

Specific Fuel Consumption given Range for Prop-Driven Aircraft is usually measured using the Kilogram per Hour per Watt[kg/h/W] for Specific Fuel Consumption. Kilogram per Second per Watt[kg/h/W], Kilogram per Second per Brake horsepower[kg/h/W], Kilogram per Hour per Kilowatt[kg/h/W] are the few other units in which Specific Fuel Consumption given Range for Prop-Driven Aircraft can be measured.

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Specific Fuel Consumption given Range for Prop-Driven Aircraft Formula

​GoSpecific Fuel Consumption for given Range of Propeller-Driven Airplane Formula

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

Specific Fuel Consumption given Range for Prop-Driven Aircraft Example

Specific Fuel Consumption given Range for Prop-Driven Aircraft Solution

Specific Fuel Consumption given Range for Prop-Driven Aircraft Formula Elements

Other Formulas to find Specific Fuel Consumption

Other formulas in Propeller Driven Airplane category

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

FAQs on Specific Fuel Consumption given Range for Prop-Driven Aircraft

Variable Name

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

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