Propeller Efficiency given Range for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary
Formula Used
Propeller Efficiency = (Range of aircraft*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
η = (R*c)/(LDmaxratio*ln(Wi/Wf))
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 aircraft - (Measured in Meter) - Range of 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 - Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.
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 aircraft: 7126 Meter --> 7126 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: 5.081 --> 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*c)/(LDmaxratio*ln(Wi/Wf)) --> (7126*0.000166666666666667)/(5.081*ln(450/350))
Evaluating ... ...
η = 0.930096371306181
STEP 3: Convert Result to Output's Unit
0.930096371306181 --> No Conversion Required
FINAL ANSWER
0.930096371306181 0.930096 <-- Propeller Efficiency
(Calculation completed in 00.004 seconds)

Credits

Created by Vedant Chitte
All India Shri Shivaji Memorials Society's ,College of Engineering (AISSMS COE PUNE), Pune
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21 Propeller-Driven Airplane Calculators

Propeller Efficiency for given Endurance of Propeller-Driven Airplane
Go 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))))
Endurance of Propeller-Driven Airplane
Go Endurance of Aircraft = Propeller Efficiency/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))
Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
Go 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))
Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft
Go Lift to Drag Ratio at Maximum Endurance = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))
Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft
Go Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance)
Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft
Go Propeller Efficiency = (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))
Specific Fuel Consumption for given Range of Propeller-Driven Airplane
Go Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel))
Range of Propeller-Driven Airplane
Go Range of 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 aircraft*Specific Fuel Consumption*Drag Coefficient/(Lift Coefficient*ln(Gross Weight/Weight without fuel))
Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft
Go Maximum Lift to Drag Ratio = (Range of aircraft*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
Propeller Efficiency given Range for Prop-Driven Aircraft
Go Propeller Efficiency = (Range of aircraft*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
Specific Fuel Consumption given Range for Prop-Driven Aircraft
Go 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 aircraft
Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Go Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
Range of Propeller-Driven Airplane for given lift-to-drag ratio
Go Range of aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Go Propeller Efficiency = Range of aircraft*Specific Fuel Consumption/(Lift-to-drag ratio*(ln(Gross Weight/Weight without fuel)))
Cruise Weight Fraction for Prop-Driven Aircraft
Go Cruise Weight Fraction = exp((Range of aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*Propeller Efficiency))
Propeller efficiency for reciprocating engine-propeller combination
Go Propeller Efficiency = Available Power/Brake Power
Shaft brake power for reciprocating engine-propeller combination
Go Brake Power = Available Power/Propeller Efficiency
Power available for reciprocating engine-propeller combination
Go Available Power = Propeller Efficiency*Brake Power
Lift to Drag Ratio for Maximum Endurance given Max Lift to Drag Ratio for Prop-driven Aircraft
Go Lift to Drag Ratio at Maximum Endurance = 0.866*Maximum Lift to Drag Ratio
Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft
Go Maximum Lift to Drag Ratio = Lift to Drag Ratio at Maximum Endurance/0.866

Propeller Efficiency given Range for Prop-Driven Aircraft Formula

Propeller Efficiency = (Range of aircraft*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
η = (R*c)/(LDmaxratio*ln(Wi/Wf))

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 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, The Propeller Efficiency given Range for Prop-Driven Aircraft formula is defined as how efficiently the propeller is converting the power from Engine to Thrust to Propel the aircraft. 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 aircraft (R), Specific Fuel Consumption (c), Maximum Lift to Drag Ratio (LDmaxratio), Weight at Start of Cruise Phase (Wi) & Weight at End of Cruise Phase (Wf) 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 -> 11.8357 = (7126*0.000166666666666667)/(5.081*ln(450/350)).

FAQ

What is Propeller Efficiency given Range for Prop-Driven Aircraft?
The Propeller Efficiency given Range for Prop-Driven Aircraft formula is defined as how efficiently the propeller is converting the power from Engine to Thrust to Propel the aircraft and is represented as η = (R*c)/(LDmaxratio*ln(Wi/Wf)) or Propeller Efficiency = (Range of aircraft*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase)). Range of 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, Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value, 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?
The Propeller Efficiency given Range for Prop-Driven Aircraft formula is defined as how efficiently the propeller is converting the power from Engine to Thrust to Propel the aircraft is calculated using Propeller Efficiency = (Range of 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 aircraft (R), Specific Fuel Consumption (c), Maximum Lift to Drag Ratio (LDmaxratio), Weight at Start of Cruise Phase (Wi) & Weight at End of Cruise Phase (Wf). With our tool, you need to enter the respective value for Range of 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 aircraft, Specific Fuel Consumption, Maximum Lift to Drag Ratio, Weight at Start of Cruise Phase & Weight at End of Cruise Phase. We can use 5 other way(s) to calculate the same, which is/are as follows -
  • Propeller Efficiency = Range of aircraft*Specific Fuel Consumption*Drag Coefficient/(Lift Coefficient*ln(Gross Weight/Weight without fuel))
  • Propeller Efficiency = Range of 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))))
  • Propeller Efficiency = Available Power/Brake Power
  • Propeller Efficiency = (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))
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