Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft Calculator

✖Preliminary Endurance of Aircraft is the time spent by the aircraft in air, or it is the endurance during preliminary design phase.ⓘ Preliminary Endurance of Aircraft [E_p]			+10% -10%
✖Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.ⓘ Velocity for Maximum Endurance [V_Emax]			+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 [c]			+10% -10%
✖Lift to Drag Ratio at Maximum Endurance is the ratio of lift to drag at which the plane can fly (or loiter) for maximum time.ⓘ Lift to Drag Ratio at Maximum Endurance [LDEmax_ratio]			+10% -10%
✖Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase.ⓘ Weight at Start of Loiter Phase [W_L,beg]			+10% -10%
✖The Weight at End of Loiter Phase refers to the aircraft's mass after completing a period of flying at a predetermined location or holding pattern.ⓘ Weight at End of Loiter Phase [W_L,end]			+10% -10%

✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft [η]

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Formula

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Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft

Formula

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

Example

0.930511 = \frac{23.4 s \cdot 15.6 m/s \cdot 0.6 kg/h/W}{4.40 \cdot \ln (\frac{400 kg}{394.1 kg})}

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Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

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))
η = (E_p*V_Emax*c)/(LDEmax_ratio*ln(W_L,beg/W_L,end))
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

Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
Preliminary Endurance of Aircraft - (Measured in Second) - Preliminary Endurance of Aircraft is the time spent by the aircraft in air, or it is the endurance during preliminary design phase.
Velocity for Maximum Endurance - (Measured in Meter per Second) - Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.
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.
Lift to Drag Ratio at Maximum Endurance - Lift to Drag Ratio at Maximum Endurance is the ratio of lift to drag at which the plane can fly (or loiter) for maximum time.
Weight at Start of Loiter Phase - (Measured in Kilogram) - Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase.
Weight at End of Loiter Phase - (Measured in Kilogram) - The Weight at End of Loiter Phase refers to the aircraft's mass after completing a period of flying at a predetermined location or holding pattern.

STEP 1: Convert Input(s) to Base Unit

Preliminary Endurance of Aircraft: 23.4 Second --> 23.4 Second No Conversion Required
Velocity for Maximum Endurance: 15.6 Meter per Second --> 15.6 Meter per Second No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Lift to Drag Ratio at Maximum Endurance: 4.4 --> No Conversion Required
Weight at Start of Loiter Phase: 400 Kilogram --> 400 Kilogram No Conversion Required
Weight at End of Loiter Phase: 394.1 Kilogram --> 394.1 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

η = (E_p*V_Emax*c)/(LDEmax_ratio*ln(W_L,beg/W_L,end)) --> (23.4*15.6*0.000166666666666667)/(4.4*ln(400/394.1))

Evaluating ... ...

η = 0.93051145988277

STEP 3: Convert Result to Output's Unit

0.93051145988277 --> No Conversion Required

FINAL ANSWER

0.93051145988277 ≈ 0.930511 <-- Propeller Efficiency

(Calculation completed in 00.004 seconds)

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All India Shri Shivaji Memorials Society's ,College of Engineering (AISSMS COE PUNE), Pune

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< Propeller Driven Airplane Calculators

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))

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 given Preliminary Endurance for Prop-Driven Aircraft Formula

What do you mean by Endurance of Aircraft?

In aviation, endurance is the maximum length of time that an aircraft can spend in a cruising flight. In other words, it is the amount of time an aircraft can stay in the air with one load of fuel. Endurance is different from range, which is a measure of distance flown. For example, a typical sailplane exhibits high endurance characteristics but poor range characteristics. Endurance can factor into aviation design in a number of ways. Some aircraft, require high endurance characteristics as part of their mission profile (often referred to as loiter time). Endurance plays a prime factor in finding out the fuel fraction for an aircraft. Endurance, like range, is also related to fuel efficiency; fuel-efficient aircraft will tend to exhibit good endurance characteristics.

What is aircraft propeller efficiency?

An aircraft propeller, also called an airscrew, converts rotary motion from an engine or other power source into a swirling slipstream which pushes the propeller forwards or backwards. It comprises a rotating power-driven hub, to which are attached several radial airfoil-section blades such that the whole assembly rotates about a longitudinal axis.

How to Calculate Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft?

Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft calculator uses 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)) to calculate the Propeller Efficiency, Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft is a measure of the efficiency of a propeller-driven aircraft's propulsion system, taking into account factors such as preliminary endurance, velocity, specific fuel consumption, lift-to-drag ratio, and aircraft weight during loitering phases, to provide a comprehensive assessment of the aircraft's overall performance. Propeller Efficiency is denoted by η symbol.

How to calculate Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft using this online calculator? To use this online calculator for Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft, enter Preliminary Endurance of Aircraft (E_p), Velocity for Maximum Endurance (V_Emax), Specific Fuel Consumption (c), Lift to Drag Ratio at Maximum Endurance (LDEmax_ratio), Weight at Start of Loiter Phase (W_L,beg) & Weight at End of Loiter Phase (W_L,end) and hit the calculate button. Here is how the Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft calculation can be explained with given input values -> 0.048168 = (23.4*15.6*0.000166666666666667)/(4.4*ln(400/394.1)).

FAQ

What is Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft?

Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft is a measure of the efficiency of a propeller-driven aircraft's propulsion system, taking into account factors such as preliminary endurance, velocity, specific fuel consumption, lift-to-drag ratio, and aircraft weight during loitering phases, to provide a comprehensive assessment of the aircraft's overall performance and is represented as η = (E_p*V_Emax*c)/(LDEmax_ratio*ln(W_L,beg/W_L,end)) or 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)). Preliminary Endurance of Aircraft is the time spent by the aircraft in air, or it is the endurance during preliminary design phase, Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance, Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Lift to Drag Ratio at Maximum Endurance is the ratio of lift to drag at which the plane can fly (or loiter) for maximum time, Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase & The Weight at End of Loiter Phase refers to the aircraft's mass after completing a period of flying at a predetermined location or holding pattern.

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

Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft is a measure of the efficiency of a propeller-driven aircraft's propulsion system, taking into account factors such as preliminary endurance, velocity, specific fuel consumption, lift-to-drag ratio, and aircraft weight during loitering phases, to provide a comprehensive assessment of the aircraft's overall performance is calculated using 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)). To calculate Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft, you need Preliminary Endurance of Aircraft (E_p), Velocity for Maximum Endurance (V_Emax), Specific Fuel Consumption (c), Lift to Drag Ratio at Maximum Endurance (LDEmax_ratio), Weight at Start of Loiter Phase (W_L,beg) & Weight at End of Loiter Phase (W_L,end). With our tool, you need to enter the respective value for Preliminary Endurance of Aircraft, Velocity for Maximum Endurance, Specific Fuel Consumption, Lift to Drag Ratio at Maximum Endurance, Weight at Start of Loiter Phase & Weight at End of Loiter Phase 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 Propeller Efficiency?

In this formula, Propeller Efficiency uses Preliminary Endurance of Aircraft, Velocity for Maximum Endurance, Specific Fuel Consumption, Lift to Drag Ratio at Maximum Endurance, Weight at Start of Loiter Phase & Weight at End of Loiter Phase. We can use 3 other way(s) to calculate the same, which is/are as follows -

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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