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Propeller Efficiency given Range for Prop-Driven Aircraft Formula

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GoPropeller Efficiency for given Range of Propeller-Driven Airplane Formula

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

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

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

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

Propeller Efficiency given Range for Prop-Driven Aircraft Example

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Here is how the Propeller Efficiency given Range for Prop-Driven Aircraft equation looks like with Values.

Here is how the Propeller Efficiency given Range for Prop-Driven Aircraft equation looks like with Units.

Here is how the Propeller Efficiency given Range for Prop-Driven Aircraft equation looks like.

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

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

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

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Propeller Efficiency given Range for Prop-Driven Aircraft Solution

Follow our step by step solution on how to calculate Propeller Efficiency given Range for Prop-Driven Aircraft?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

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

Next Step Convert Units

∴

η = \frac{7126.017m \cdot 0.0002kg/s/W}{5.0815 \cdot \ln (\frac{450kg}{350kg})}

Next Step Prepare to Evaluate

∴

η = \frac{7126.017 \cdot 0.0002}{5.0815 \cdot \ln (\frac{450}{350})}

Next Step Evaluate

∴

η = 0.93000213059269

LAST Step Rounding Answer

∴

η = 0.93

Propeller Efficiency given Range for Prop-Driven Aircraft Formula Elements

Variables

Functions

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

Open Variable

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

Open Variable

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

Open Variable

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

Open Variable

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

Open Variable

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

Open Variable

ln

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 Propeller Efficiency

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 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}))}

Go Propeller Efficiency for given Endurance of Propeller-Driven Airplane

η = \frac{E}{(\frac{1}{c}) \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 Propeller Efficiency for Reciprocating Engine-Propeller Combination

η = \frac{P A}{BP}

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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 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 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 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}))

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OpenImg

How to Evaluate Propeller Efficiency given Range for Prop-Driven Aircraft?

Propeller Efficiency given Range for Prop-Driven Aircraft evaluator uses 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)) to evaluate the Propeller Efficiency, Propeller Efficiency given Range for Prop-Driven Aircraft is a measure of the effectiveness of a propeller-powered aircraft in converting engine power into useful work, taking into account the range of the aircraft, specific fuel consumption, maximum lift-to-drag ratio, and aircraft weight changes during cruise, this efficiency metric helps aircraft designers and engineers optimize propeller design for improved fuel efficiency and overall performance. Propeller Efficiency is denoted by η symbol.

How to evaluate Propeller Efficiency given Range for Prop-Driven Aircraft using this online evaluator? To use this online evaluator for Propeller Efficiency given Range for Prop-Driven Aircraft, enter Range of Propeller Aircraft (R_prop), Specific Fuel Consumption (c), Maximum Lift-to-Drag Ratio (LDmax_ratio), Weight at Start of Cruise Phase (W_i) & Weight at End of Cruise Phase (W_f) and hit the calculate button.

FAQs on Propeller Efficiency given Range for Prop-Driven Aircraft

What is the formula to find Propeller Efficiency given Range for Prop-Driven Aircraft?

The formula of Propeller Efficiency given Range for Prop-Driven Aircraft is expressed as 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)). Here is an example- 0.930099 = (7126.017*0.000166666666666667)/(5.081527*ln(450/350)).

How to calculate Propeller Efficiency given Range for Prop-Driven Aircraft?

With Range of Propeller Aircraft (R_prop), Specific Fuel Consumption (c), Maximum Lift-to-Drag Ratio (LDmax_ratio), Weight at Start of Cruise Phase (W_i) & Weight at End of Cruise Phase (W_f) we can find Propeller Efficiency given Range for Prop-Driven Aircraft using the formula - 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)). This formula also uses Natural Logarithm (ln) function(s).

What are the other ways to Calculate Propeller Efficiency?

Here are the different ways to Calculate Propeller Efficiency-

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

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