Specific Fuel Consumption given Range for Prop-Driven Aircraft Calculator

↳

⤿

Aircraft Performance

Aircraft Design

Introduction and Governing Equations

Static Stability and Control

⤿

⤿

Propeller-Driven Airplane

Jet Airplane

✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+10% -10%
✖Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.ⓘ 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%
✖Range of aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Range of aircraft [R]			+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 Range for Prop-Driven Aircraft [c]

⎘ Copy

👎

Formula

✖

Specific Fuel Consumption given Range for Prop-Driven Aircraft

Formula

`"c" = ("η"*"LDmax"_{"ratio"}*ln("W"_{"i"}/"W"_{"f"}))/"R"`

Example

`"0.599938kg/h/W"=("0.93"*"5.081"*ln("450kg"/"350kg"))/"7126m"`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF

Specific Fuel Consumption given Range for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

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
c = (η*LDmax_ratio*ln(W_i/W_f))/R
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

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.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
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.
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.

STEP 1: Convert Input(s) to Base Unit

Propeller Efficiency: 0.93 --> No Conversion Required
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
Range of aircraft: 7126 Meter --> 7126 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c = (η*LDmax_ratio*ln(W_i/W_f))/R --> (0.93*5.081*ln(450/350))/7126

Evaluating ... ...

c = 0.000166649397612772

STEP 3: Convert Result to Output's Unit

0.000166649397612772 Kilogram per Second per Watt -->0.59993783140598 Kilogram per Hour per Watt (Check conversion here)

FINAL ANSWER

0.59993783140598 ≈ 0.599938 Kilogram per Hour per Watt <-- Specific Fuel Consumption

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Performance » Range and Endurance » Propeller-Driven Airplane » Specific Fuel Consumption given Range for Prop-Driven Aircraft

Credits

Created by Vedant Chitte

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

Vedant Chitte has created this Calculator and 25+ more calculators!

Verified by Ravi Khiyani

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

Ravi Khiyani has verified this Calculator and 300+ more calculators!

< 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))

Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft

Go Propeller Efficiency = (Preliminary 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))

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)

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

Specific Fuel Consumption given Range for Prop-Driven Aircraft Formula

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
c = (η*LDmax_ratio*ln(W_i/W_f))/R

What is Specific Fuel Consumption?

The Specific Fuel Consumption (SFC) is a technical figure of merit for an engine that indicates how efficiently the engine is burning fuel and converting it to thrust. SFC depends on the type and design technology of the engine and also the type of fuel. SFC is used to describe the fuel efficiency of an engine with respect to its mechanical output.

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

Specific Fuel Consumption given Range for Prop-Driven Aircraft calculator uses 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 to calculate the Specific Fuel Consumption, The Specific Fuel Consumption given Range for Prop-Driven Aircraft formula is defined as the fuel consumed by the engine over a unit of time to produce a specific amount of thrust. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption given Range for Prop-Driven Aircraft using this online calculator? To use this online calculator for Specific Fuel Consumption given Range for Prop-Driven Aircraft, enter Propeller Efficiency (η), Maximum Lift to Drag Ratio (LDmax_ratio), Weight at Start of Cruise Phase (W_i), Weight at End of Cruise Phase (W_f) & Range of aircraft (R) and hit the calculate button. Here is how the Specific Fuel Consumption given Range for Prop-Driven Aircraft calculation can be explained with given input values -> 169.7239 = (0.93*5.081*ln(450/350))/7126.

FAQ

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

The Specific Fuel Consumption given Range for Prop-Driven Aircraft formula is defined as the fuel consumed by the engine over a unit of time to produce a specific amount of thrust and is represented as c = (η*LDmax_ratio*ln(W_i/W_f))/R or 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. Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), 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 & Range of aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.

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

The Specific Fuel Consumption given Range for Prop-Driven Aircraft formula is defined as the fuel consumed by the engine over a unit of time to produce a specific amount of thrust is calculated using 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. To calculate Specific Fuel Consumption given Range for Prop-Driven Aircraft, you need Propeller Efficiency (η), Maximum Lift to Drag Ratio (LDmax_ratio), Weight at Start of Cruise Phase (W_i), Weight at End of Cruise Phase (W_f) & Range of aircraft (R). With our tool, you need to enter the respective value for Propeller Efficiency, Maximum Lift to Drag Ratio, Weight at Start of Cruise Phase, Weight at End of Cruise Phase & Range of aircraft 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, Maximum Lift to Drag Ratio, Weight at Start of Cruise Phase, Weight at End of Cruise Phase & Range of aircraft. We can use 4 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))
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))
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)

Home

FREE PDFs

🔍 Search