Propeller Efficiency given Range for Prop-Driven Aircraft Calculator

✖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 [c]			+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%

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

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Propeller Efficiency given Range for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

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))
η = (R_prop*c)/(LDmax_ratio*ln(W_i/W_f))
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

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.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Range of Propeller Aircraft: 7126.017 Meter --> 7126.017 Meter No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

η = (R_prop*c)/(LDmax_ratio*ln(W_i/W_f)) --> (7126.017*0.000166666666666667)/(5.081527*ln(450/350))

Evaluating ... ...

η = 0.93000213059269

STEP 3: Convert Result to Output's Unit

0.93000213059269 --> No Conversion Required

FINAL ANSWER

0.93000213059269 ≈ 0.930002 <-- 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

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))

Propeller Efficiency given Range for Prop-Driven Aircraft Formula

LaTeX Go

What do mean by Propeller?

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. The blade pitch may be fixed, manually variable to a few set positions, or of the automatically variable "constant-speed" type.
The propeller attaches to the power source's driveshaft either directly or through reduction gearing. Propellers can be made from wood, metal or composite materials.

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

Propeller Efficiency given Range for Prop-Driven Aircraft calculator 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 calculate 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 calculate Propeller Efficiency given Range for Prop-Driven Aircraft using this online calculator? To use this online calculator 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. Here is how the Propeller Efficiency given Range for Prop-Driven Aircraft calculation can be explained with given input values -> 0.930099 = (7126.017*0.000166666666666667)/(5.081527*ln(450/350)).

FAQ

What is Propeller Efficiency given Range for Prop-Driven Aircraft?

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 and is represented as η = (R_prop*c)/(LDmax_ratio*ln(W_i/W_f)) or 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)). Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, 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.

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

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 is calculated using 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 calculate Propeller Efficiency given Range for Prop-Driven Aircraft, you need 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). With our tool, you need to enter the respective value for Range of Propeller Aircraft, Specific Fuel Consumption, Maximum Lift-to-Drag Ratio, Weight at Start of Cruise Phase & Weight at End of Cruise 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 Range of Propeller Aircraft, Specific Fuel Consumption, Maximum Lift-to-Drag Ratio, Weight at Start of Cruise Phase & Weight at End of Cruise 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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