Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft Calculator

✖Lift to Drag Ratio at Maximum Endurance Prop 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 Prop [LDEmax_{ratio prop}]			+10% -10%
✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+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%
✖Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.ⓘ Endurance of Aircraft [E]			+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 given Preliminary Endurance for Prop-Driven Aircraft [c]

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Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance Prop*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance)
c = (LDEmax_{ratio prop}*η*ln(W_L,beg/W_L,end))/(E*V_Emax)
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

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 Prop - Lift to Drag Ratio at Maximum Endurance Prop is the ratio of lift to drag at which the plane can fly (or loiter) for maximum time.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
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.
Endurance of Aircraft - (Measured in Second) - Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.
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.

STEP 1: Convert Input(s) to Base Unit

Lift to Drag Ratio at Maximum Endurance Prop: 85.04913 --> No Conversion Required
Propeller Efficiency: 0.93 --> 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
Endurance of Aircraft: 452.0581 Second --> 452.0581 Second No Conversion Required
Velocity for Maximum Endurance: 15.6 Meter per Second --> 15.6 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c = (LDEmax_{ratio prop}*η*ln(W_L,beg/W_L,end))/(E*V_Emax) --> (85.04913*0.93*ln(400/394.1))/(452.0581*15.6)

Evaluating ... ...

c = 0.000166666675644176

STEP 3: Convert Result to Output's Unit

0.000166666675644176 Kilogram per Second per Watt -->0.600000032319033 Kilogram per Hour per Watt (Check conversion here)

FINAL ANSWER

0.600000032319033 ≈ 0.6 Kilogram per Hour per Watt <-- Specific Fuel Consumption

(Calculation completed in 00.004 seconds)

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Created by Vedant Chitte

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

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Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore

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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))

Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft Formula

LaTeX Go

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.

How to Calculate Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft?

Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft calculator uses Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance Prop*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance) to calculate the Specific Fuel Consumption, Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft is a measure of the amount of fuel consumed by an aircraft per unit of time, taking into account the lift-to-drag ratio, propeller efficiency, and the weight and velocity of the aircraft during maximum endurance, enabling the calculation of fuel requirements for optimal performance. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft using this online calculator? To use this online calculator for Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft, enter Lift to Drag Ratio at Maximum Endurance Prop (LDEmax_{ratio prop}), Propeller Efficiency (η), Weight at Start of Loiter Phase (W_L,beg), Weight at End of Loiter Phase (W_L,end), Endurance of Aircraft (E) & Velocity for Maximum Endurance (V_Emax) and hit the calculate button. Here is how the Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft calculation can be explained with given input values -> 111.7472 = (85.04913*0.93*ln(400/394.1))/(452.0581*15.6).

FAQ

What is Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft?

Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft is a measure of the amount of fuel consumed by an aircraft per unit of time, taking into account the lift-to-drag ratio, propeller efficiency, and the weight and velocity of the aircraft during maximum endurance, enabling the calculation of fuel requirements for optimal performance and is represented as c = (LDEmax_{ratio prop}*η*ln(W_L,beg/W_L,end))/(E*V_Emax) or Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance Prop*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance). Lift to Drag Ratio at Maximum Endurance Prop is the ratio of lift to drag at which the plane can fly (or loiter) for maximum time, Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), 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, Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight & Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.

How to calculate Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft?

Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft is a measure of the amount of fuel consumed by an aircraft per unit of time, taking into account the lift-to-drag ratio, propeller efficiency, and the weight and velocity of the aircraft during maximum endurance, enabling the calculation of fuel requirements for optimal performance is calculated using Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance Prop*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance). To calculate Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft, you need Lift to Drag Ratio at Maximum Endurance Prop (LDEmax_{ratio prop}), Propeller Efficiency (η), Weight at Start of Loiter Phase (W_L,beg), Weight at End of Loiter Phase (W_L,end), Endurance of Aircraft (E) & Velocity for Maximum Endurance (V_Emax). With our tool, you need to enter the respective value for Lift to Drag Ratio at Maximum Endurance Prop, Propeller Efficiency, Weight at Start of Loiter Phase, Weight at End of Loiter Phase, Endurance of Aircraft & Velocity for Maximum Endurance 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 Lift to Drag Ratio at Maximum Endurance Prop, Propeller Efficiency, Weight at Start of Loiter Phase, Weight at End of Loiter Phase, Endurance of Aircraft & Velocity for Maximum Endurance. We can use 3 other way(s) to calculate the same, which is/are as follows -

Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel))
Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel))
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))

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