Fuel Fraction Calculator

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Preliminary Design

Conceptual Design

✖Fuel Weight to be Carried is defined as the total mass of the fuel to be carried (usually includes reserve fuel).ⓘ Fuel Weight to be Carried [FW]			+10% -10%
✖Desired Takeoff Weight (or mass) is the weight of the aircraft.ⓘ Desired Takeoff Weight [DTW]			+10% -10%

✖Fuel Fraction is the ratio between weight of fuel caried by a plane to the aircraft total take off weight.ⓘ Fuel Fraction [F_f]

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Formula

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Fuel Fraction

Formula

`"F"_{"f"} = "FW"/"DTW"`

Example

`"0.0044"="1100kg"/"250000kg"`

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Fuel Fraction Solution

STEP 0: Pre-Calculation Summary

Formula Used

Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight
F_f = FW/DTW
This formula uses 3 Variables

Variables Used

Fuel Fraction - Fuel Fraction is the ratio between weight of fuel caried by a plane to the aircraft total take off weight.
Fuel Weight to be Carried - (Measured in Kilogram) - Fuel Weight to be Carried is defined as the total mass of the fuel to be carried (usually includes reserve fuel).
Desired Takeoff Weight - (Measured in Kilogram) - Desired Takeoff Weight (or mass) is the weight of the aircraft.

STEP 1: Convert Input(s) to Base Unit

Fuel Weight to be Carried: 1100 Kilogram --> 1100 Kilogram No Conversion Required
Desired Takeoff Weight: 250000 Kilogram --> 250000 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_f = FW/DTW --> 1100/250000

Evaluating ... ...

F_f = 0.0044

STEP 3: Convert Result to Output's Unit

0.0044 --> No Conversion Required

FINAL ANSWER

0.0044 <-- Fuel Fraction

(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

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

Verified by Ravi Khiyani

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

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< 25 Preliminary Design Calculators

Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft

Go Velocity for Maximum Endurance = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Endurance of Aircraft)

Preliminary Endurance for Prop-Driven Aircraft

Go Endurance of Aircraft = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Velocity for Maximum Endurance)

Velocity for Maximizing Range given Range for Jet Aircraft

Go Velocity at Maximum Lift to Drag Ratio = (Range of Aircraft*Power Specific Fuel Consumption)/(Maximum Lift to Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase))

Optimum Range for Jet Aircraft in Cruising Phase

Go Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)

Optimum Range for Prop-Driven Aircraft in Cruising Phase

Go Range of Aircraft = (Propeller Efficiency*Maximum Lift to Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)

Preliminary Endurance for Jet Aircraft

Go Endurance of Aircraft = (Maximum Lift to Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase))/Power Specific Fuel Consumption

Maximum Lift over Drag

Go Maximum Lift to Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5)

Preliminary Take Off Weight Built-up for Manned Aircraft

Go Desired Takeoff Weight = Payload Carried+Operating Empty Weight+Fuel Weight to be Carried+Crew Weight

Payload Weight given Takeoff Weight

Go Payload Carried = Desired Takeoff Weight-Operating Empty Weight-Crew Weight-Fuel Weight to be Carried

Empty Weight given Takeoff Weight

Go Operating Empty Weight = Desired Takeoff Weight-Fuel Weight to be Carried-Payload Carried-Crew Weight

Crew Weight given Takeoff Weight

Go Crew Weight = Desired Takeoff Weight-Payload Carried-Fuel Weight to be Carried-Operating Empty Weight

Fuel Weight given Takeoff Weight

Go Fuel Weight to be Carried = Desired Takeoff Weight-Operating Empty Weight-Payload Carried-Crew Weight

Preliminary Take off Weight Built-Up for Manned Aircraft given Fuel and Empty Weight Fraction

Go Desired Takeoff Weight = (Payload Carried+Crew Weight)/(1-Fuel Fraction-Empty Weight Fraction)

Fuel Fraction given Takeoff Weight and Empty Weight Fraction

Go Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight

Empty Weight Fraction given Takeoff Weight and Fuel Fraction

Go Empty Weight Fraction = 1-Fuel Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight

Payload Weight given Fuel and Empty Weight Fractions

Go Payload Carried = Desired Takeoff Weight*(1-Empty Weight Fraction-Fuel Fraction)-Crew Weight

Crew Weight given Fuel and Empty Weight Fraction

Go Crew Weight = Desired Takeoff Weight*(1-Empty Weight Fraction-Fuel Fraction)-Payload Carried

Takeoff Weight given Empty Weight Fraction

Go Desired Takeoff Weight = Operating Empty Weight/Empty Weight Fraction

Empty Weight given Empty Weight Fraction

Go Operating Empty Weight = Empty Weight Fraction*Desired Takeoff Weight

Empty Weight Fraction

Go Empty Weight Fraction = Operating Empty Weight/Desired Takeoff Weight

Winglet Friction Coefficient

Go Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58))

Takeoff Weight given Fuel Fraction

Go Desired Takeoff Weight = Fuel Weight to be Carried/Fuel Fraction

Fuel Weight given Fuel Fraction

Go Fuel Weight to be Carried = Fuel Fraction*Desired Takeoff Weight

Fuel Fraction

Go Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight

Design range given range increment

Go Design range = Range increment of aircraft+Harmonic range

Fuel Fraction Formula

Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight
F_f = FW/DTW

What is Fuel Weight?

The total weight of fuel carried by an aircraft during whole flight is called as fuel weight. The fuel weight varies with the flight, as the fuel is burnt in the engines the weight of fuel reduces. For Fuel Fraction the maximum amount of fuel is considered.

What is Importance of Fuel Fraction?

In aerospace engineering, an aircraft's fuel fraction, fuel weight fraction, or a spacecraft's propellant fraction, is the weight of the fuel or propellant divided by the gross take-off weight of the craft (including propellant).
The fractional result of this mathematical division. For aircraft with external drop tanks, the term internal fuel fraction is used to exclude the weight of external tanks and fuel.
Fuel fraction is a key parameter in determining an aircraft's range, the distance it can fly without refueling. Breguet’s aircraft range equation describes the relationship of range with airspeed, lift-to-drag ratio, specific fuel consumption, and the part of the total fuel fraction available for cruise, also known as the cruise fuel fraction, or cruise fuel weight fraction.

How to Calculate Fuel Fraction?

Fuel Fraction calculator uses Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight to calculate the Fuel Fraction, The Fuel Fraction (Preliminary Design) formula is defined as the ratio of the fuel weight carried by the plane to the total takeoff weight of the plane. Fuel Fraction is denoted by F_f symbol.

How to calculate Fuel Fraction using this online calculator? To use this online calculator for Fuel Fraction, enter Fuel Weight to be Carried (FW) & Desired Takeoff Weight (DTW) and hit the calculate button. Here is how the Fuel Fraction calculation can be explained with given input values -> 0.0044 = 1100/250000.

FAQ

What is Fuel Fraction?

The Fuel Fraction (Preliminary Design) formula is defined as the ratio of the fuel weight carried by the plane to the total takeoff weight of the plane and is represented as F_f = FW/DTW or Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight. Fuel Weight to be Carried is defined as the total mass of the fuel to be carried (usually includes reserve fuel) & Desired Takeoff Weight (or mass) is the weight of the aircraft.

How to calculate Fuel Fraction?

The Fuel Fraction (Preliminary Design) formula is defined as the ratio of the fuel weight carried by the plane to the total takeoff weight of the plane is calculated using Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight. To calculate Fuel Fraction, you need Fuel Weight to be Carried (FW) & Desired Takeoff Weight (DTW). With our tool, you need to enter the respective value for Fuel Weight to be Carried & Desired Takeoff Weight 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 Fuel Fraction?

In this formula, Fuel Fraction uses Fuel Weight to be Carried & Desired Takeoff Weight. We can use 1 other way(s) to calculate the same, which is/are as follows -

Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight

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