Specific Fuel Consumption given Range for Jet Aircraft Calculator

✖Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.ⓘ Velocity at Maximum Lift to Drag Ratio [V_L/D,max]			+10% -10%
✖The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.ⓘ 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 Jet Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Range of Jet Aircraft [R_jet]			+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 Jet Aircraft [c]

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Specific Fuel Consumption given Range for Jet Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of Jet Aircraft
c = (V_L/D,max*LDmax_ratio*ln(W_i/W_f))/R_jet
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.
Velocity at Maximum Lift to Drag Ratio - (Measured in Meter per Second) - Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.
Maximum Lift-to-Drag Ratio - The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.
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 Jet Aircraft - (Measured in Meter) - Range of Jet 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

Velocity at Maximum Lift to Drag Ratio: 1.05 Meter per Second --> 1.05 Meter per Second No Conversion Required
Maximum Lift-to-Drag Ratio: 5.081527 --> 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 Jet Aircraft: 7130 Meter --> 7130 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c = (V_L/D,max*LDmax_ratio*ln(W_i/W_f))/R_jet --> (1.05*5.081527*ln(450/350))/7130

Evaluating ... ...

c = 0.000188066494451464

STEP 3: Convert Result to Output's Unit

0.000188066494451464 Kilogram per Second per Watt -->0.67703938002527 Kilogram per Hour per Watt (Check conversion here)

FINAL ANSWER

0.67703938002527 ≈ 0.677039 Kilogram per Hour per Watt <-- Specific Fuel Consumption

(Calculation completed in 00.023 seconds)

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

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< Jet Airplane Calculators

Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

LaTeX Go Thrust-Specific Fuel Consumption = Lift Coefficient*(ln(Gross Weight/Weight without Fuel))/(Drag Coefficient*Endurance of Aircraft)

Endurance of Jet Airplane

LaTeX Go Endurance of Aircraft = Lift Coefficient*(ln(Gross Weight/Weight without Fuel))/(Drag Coefficient*Thrust-Specific Fuel Consumption)

Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag Ratio of Jet Airplane

LaTeX Go Thrust-Specific Fuel Consumption = (1/Endurance of Aircraft)*Lift-to-Drag Ratio*ln(Gross Weight/Weight without Fuel)

Endurance for given Lift-to-Drag Ratio of Jet Airplane

LaTeX Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*Lift-to-Drag Ratio*ln(Gross Weight/Weight without Fuel)

Specific Fuel Consumption given Range for Jet Aircraft Formula

LaTeX Go

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 Jet Aircraft?

Specific Fuel Consumption given Range for Jet Aircraft calculator uses Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of Jet Aircraft to calculate the Specific Fuel Consumption, Specific Fuel Consumption given Range for Jet Aircraft is a measure of the fuel efficiency of a jet aircraft, calculated as the ratio of the maximum lift-to-drag ratio at the end of the range, the natural logarithm of the ratio of the beginning and ending aircraft weights, and the range of the jet aircraft, providing a valuable indicator of an aircraft's performance and efficiency. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption given Range for Jet Aircraft using this online calculator? To use this online calculator for Specific Fuel Consumption given Range for Jet Aircraft, enter Velocity at Maximum Lift to Drag Ratio (V_L/D,max), 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 Jet Aircraft (R_jet) and hit the calculate button. Here is how the Specific Fuel Consumption given Range for Jet Aircraft calculation can be explained with given input values -> 2437.089 = (1.05*5.081527*ln(450/350))/7130.

FAQ

What is Specific Fuel Consumption given Range for Jet Aircraft?

Specific Fuel Consumption given Range for Jet Aircraft is a measure of the fuel efficiency of a jet aircraft, calculated as the ratio of the maximum lift-to-drag ratio at the end of the range, the natural logarithm of the ratio of the beginning and ending aircraft weights, and the range of the jet aircraft, providing a valuable indicator of an aircraft's performance and efficiency and is represented as c = (V_L/D,max*LDmax_ratio*ln(W_i/W_f))/R_jet or Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of Jet Aircraft. Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase, The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve, 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 Jet 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 Jet Aircraft?

Specific Fuel Consumption given Range for Jet Aircraft is a measure of the fuel efficiency of a jet aircraft, calculated as the ratio of the maximum lift-to-drag ratio at the end of the range, the natural logarithm of the ratio of the beginning and ending aircraft weights, and the range of the jet aircraft, providing a valuable indicator of an aircraft's performance and efficiency is calculated using Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of Jet Aircraft. To calculate Specific Fuel Consumption given Range for Jet Aircraft, you need Velocity at Maximum Lift to Drag Ratio (V_L/D,max), 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 Jet Aircraft (R_jet). With our tool, you need to enter the respective value for Velocity at Maximum Lift to Drag Ratio, Maximum Lift-to-Drag Ratio, Weight at Start of Cruise Phase, Weight at End of Cruise Phase & Range of Jet 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 Velocity at Maximum Lift to Drag Ratio, Maximum Lift-to-Drag Ratio, Weight at Start of Cruise Phase, Weight at End of Cruise Phase & Range of Jet Aircraft. We can use 1 other way(s) to calculate the same, which is/are as follows -

Specific Fuel Consumption = (Maximum Lift-to-Drag Ratio*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/Endurance of Aircraft

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