Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Range and Endurance of Propeller-Driven Airplane ↺

✖Propeller efficiency is defined as power produced (propeller power) divided by power applied (engine power)ⓘ Propeller efficiency [η]			+10% -10%
✖Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flightⓘ Endurance of aircraft [E]			+10% -10%
✖The lift coefficient (CL) 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%
✖The Gross Weight of the airplane is the weight with full fuel and payloadⓘ Gross Weight [W₀]			+10% -10%
✖Weight without fuel is the total weight of the airplane without fuelⓘ Weight without fuel [W₁]			+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 for given Endurance of Propeller-Driven Airplane [c]

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Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 200+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given zero-lift drag coefficient

Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO

Drag Coefficient for given parasite drag coefficient

Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO

Coefficient of Drag due to lift

Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO

Parasite Drag Coefficient at zero lift

Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO

Thrust required for level, unaccelerated flight

Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO

Dynamic pressure based on coefficient of lift

Dynamic Pressure=Lift force/(lift coefficient*Area) GO

Dynamic pressure

Dynamic Pressure=Drag Force/(Drag Coefficient*Area) GO

Drag for a level, unaccelerated flight at negligible thrust angle

Drag Force=Dynamic Pressure*Area*Drag Coefficient GO

Lift for a level, unaccelerated flight at negligible thrust angle

Lift force=Dynamic Pressure*Area*lift coefficient GO

Lift Force

Lift force=lift coefficient*Dynamic Pressure*Area GO

Drag force

Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

< 2 Other formulas that calculate the same Output

Specific Fuel Consumption for given Range of Propeller-Driven Airplane

Specific Fuel Consumption=(Propeller efficiency/Range of aircraft)*(lift coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel)) GO

Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane

Specific Fuel Consumption=(Propeller efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel)) GO

Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane Formula

Specific Fuel Consumption=(Propeller efficiency/Endurance of aircraft)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2)))
c=(η/E)*((CL^1.5)/CD)*(sqrt(2*ρ∞*S))*(((1/W0)^(1/2))-((1/W1)^(1/2)))

More formulas

Range of Propeller-Driven Airplane GO

Propeller Efficiency for given Range of Propeller-Driven Airplane GO

Specific Fuel Consumption for given Range of Propeller-Driven Airplane GO

Range of Propeller-Driven Airplane for given lift-to-drag ratio GO

Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane GO

Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane GO

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane GO

Endurance of Propeller-Driven Airplane GO

Propeller Efficiency for given Endurance of Propeller-Driven Airplane GO

What is the best endurance speed?

The speed which gives the minimum drag for given aircraft weight and altitude is called best endurance speed. Flying at higher speeds than the best endurance speed increases the drag and the fuel flow, and therefore reduces the endurance.

How to Calculate Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane?

Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane calculator uses Specific Fuel Consumption=(Propeller efficiency/Endurance of aircraft)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2))) to calculate the Specific Fuel Consumption, The Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane can be obtained from the Breguet endurance formula and is a function of the altitude of aircraft. Specific Fuel Consumption and is denoted by c symbol.

How to calculate Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane using this online calculator? To use this online calculator for Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane, enter Propeller efficiency (η), Endurance of aircraft (E), lift coefficient (C_L), Drag Coefficient (C_D), Freestream density (ρ_∞), Reference Area (S), Gross Weight (W₀) and Weight without fuel (W₁) and hit the calculate button. Here is how the Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane calculation can be explained with given input values -> -3.937E-7 = (0.93/2000)*((10^1.5)/100)*(sqrt(2*1.225*5))*(((1/5000)^(1/2))-((1/4500)^(1/2))).

FAQ

What is Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane?

The Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane can be obtained from the Breguet endurance formula and is a function of the altitude of aircraft and is represented as c=(η/E)*((C_L^1.5)/C_D)*(sqrt(2*ρ_∞*S))*(((1/W₀)^(1/2))-((1/W₁)^(1/2))) or Specific Fuel Consumption=(Propeller efficiency/Endurance of aircraft)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2))). Propeller efficiency is defined as power produced (propeller power) divided by power applied (engine power), Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flight, The lift coefficient (CL) 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, The Gross Weight of the airplane is the weight with full fuel and payload and Weight without fuel is the total weight of the airplane without fuel.

How to calculate Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane?

The Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane can be obtained from the Breguet endurance formula and is a function of the altitude of aircraft is calculated using Specific Fuel Consumption=(Propeller efficiency/Endurance of aircraft)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2))). To calculate Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane, you need Propeller efficiency (η), Endurance of aircraft (E), lift coefficient (C_L), Drag Coefficient (C_D), Freestream density (ρ_∞), Reference Area (S), Gross Weight (W₀) and Weight without fuel (W₁). With our tool, you need to enter the respective value for Propeller efficiency, Endurance of aircraft, lift coefficient, Drag Coefficient, Freestream density, Reference Area, Gross Weight and Weight without fuel 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 Specific Fuel Consumption?

In this formula, Specific Fuel Consumption uses Propeller efficiency, Endurance of aircraft, lift coefficient, Drag Coefficient, Freestream density, Reference Area, Gross Weight and Weight without fuel. We can use 2 other way(s) to calculate the same, which is/are as follows -

Specific Fuel Consumption=(Propeller efficiency/Range of aircraft)*(lift coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel))
Specific Fuel Consumption=(Propeller efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))

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