Endurance of Propeller-Driven Airplane Calculator

✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+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 Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.ⓘ Lift Coefficient [C_L]			+10% -10%
✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%
✖Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream Density [ρ_∞]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖Weight without Fuel is the total weight of the airplane without fuel.ⓘ Weight without Fuel [W₁]			+10% -10%
✖The Gross Weight of the airplane is the weight with full fuel and payload.ⓘ Gross Weight [W₀]			+10% -10%

✖Endurance of Propeller Aircraft is the maximum length of time that an aircraft can spend in cruising flight.ⓘ Endurance of Propeller-Driven Airplane [E_prop]

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Endurance of Propeller-Driven Airplane Solution

STEP 0: Pre-Calculation Summary

Formula Used

Endurance of Propeller 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))
E_prop = η/c*(C_L^1.5)/C_D*sqrt(2*ρ_∞*S)*((1/W₁)^(1/2)-(1/W₀)^(1/2))
This formula uses 1 Functions, 9 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Endurance of Propeller Aircraft - (Measured in Second) - Endurance of Propeller Aircraft is the maximum length of time that an aircraft can spend in cruising flight.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
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 Coefficient - The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
Freestream Density - (Measured in Kilogram per Cubic Meter) - Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Weight without Fuel - (Measured in Kilogram) - Weight without Fuel is the total weight of the airplane without fuel.
Gross Weight - (Measured in Kilogram) - The Gross Weight of the airplane is the weight with full fuel and payload.

STEP 1: Convert Input(s) to Base Unit

Propeller Efficiency: 0.93 --> No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Lift Coefficient: 5 --> No Conversion Required
Drag Coefficient: 2 --> No Conversion Required
Freestream Density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Reference Area: 5.11 Square Meter --> 5.11 Square Meter No Conversion Required
Weight without Fuel: 3000 Kilogram --> 3000 Kilogram No Conversion Required
Gross Weight: 5000 Kilogram --> 5000 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

E_prop = η/c*(C_L^1.5)/C_D*sqrt(2*ρ_∞*S)*((1/W₁)^(1/2)-(1/W₀)^(1/2)) --> 0.93/0.000166666666666667*(5^1.5)/2*sqrt(2*1.225*5.11)*((1/3000)^(1/2)-(1/5000)^(1/2))

Evaluating ... ...

E_prop = 454.205515825231

STEP 3: Convert Result to Output's Unit

454.205515825231 Second --> No Conversion Required

FINAL ANSWER

454.205515825231 ≈ 454.2055 Second <-- Endurance of Propeller Aircraft

(Calculation completed in 00.216 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), 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))

Endurance of Propeller-Driven Airplane Formula

LaTeX Go

What is the difference between the range and the endurance of an aircraft?

Endurance is the measure of how long any aerial vehicle can stay aloft, it is a measure of time (hours, minutes, seconds). The range is how far an aerial vehicle can get on a load of fuel, it is a measure of distance (miles, kilometers, yards, and meters).

How to Calculate Endurance of Propeller-Driven Airplane?

Endurance of Propeller-Driven Airplane calculator uses Endurance of Propeller 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)) to calculate the Endurance of Propeller Aircraft, Endurance of Propeller-Driven Airplane is a measure of the time an aircraft can stay aloft, which depends on factors such as propeller efficiency, specific fuel consumption, lift coefficient, drag coefficient, and aircraft weight. Endurance of Propeller Aircraft is denoted by E_prop symbol.

How to calculate Endurance of Propeller-Driven Airplane using this online calculator? To use this online calculator for Endurance of Propeller-Driven Airplane, enter Propeller Efficiency (η), Specific Fuel Consumption (c), Lift Coefficient (C_L), Drag Coefficient (C_D), Freestream Density (ρ_∞), Reference Area (S), Weight without Fuel (W₁) & Gross Weight (W₀) and hit the calculate button. Here is how the Endurance of Propeller-Driven Airplane calculation can be explained with given input values -> 454.2055 = 0.93/0.000166666666666667*(5^1.5)/2*sqrt(2*1.225*5.11)*((1/3000)^(1/2)-(1/5000)^(1/2)).

FAQ

What is Endurance of Propeller-Driven Airplane?

Endurance of Propeller-Driven Airplane is a measure of the time an aircraft can stay aloft, which depends on factors such as propeller efficiency, specific fuel consumption, lift coefficient, drag coefficient, and aircraft weight and is represented as E_prop = η/c*(C_L^1.5)/C_D*sqrt(2*ρ_∞*S)*((1/W₁)^(1/2)-(1/W₀)^(1/2)) or Endurance of Propeller 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)). Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area, Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water, Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, Weight without Fuel is the total weight of the airplane without fuel & The Gross Weight of the airplane is the weight with full fuel and payload.

How to calculate Endurance of Propeller-Driven Airplane?

Endurance of Propeller-Driven Airplane is a measure of the time an aircraft can stay aloft, which depends on factors such as propeller efficiency, specific fuel consumption, lift coefficient, drag coefficient, and aircraft weight is calculated using Endurance of Propeller 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)). To calculate Endurance of Propeller-Driven Airplane, you need Propeller Efficiency (η), Specific Fuel Consumption (c), Lift Coefficient (C_L), Drag Coefficient (C_D), Freestream Density (ρ_∞), Reference Area (S), Weight without Fuel (W₁) & Gross Weight (W₀). With our tool, you need to enter the respective value for Propeller Efficiency, Specific Fuel Consumption, Lift Coefficient, Drag Coefficient, Freestream Density, Reference Area, Weight without Fuel & Gross Weight and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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