Takeoff Weight given Fuel Fraction Calculator

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✖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%
✖Fuel Fraction is the ratio between weight of fuel caried by a plane to the aircraft total take off weight.ⓘ Fuel Fraction [F_f]			+10% -10%

✖Desired Takeoff Weight (or mass) is the weight of the aircraft.ⓘ Takeoff Weight given Fuel Fraction [DTW]

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Formula

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Takeoff Weight given Fuel Fraction

Formula

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

Example

`"250000kg"="100000kg"/"0.4"`

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Takeoff Weight given Fuel Fraction Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Desired Takeoff Weight - (Measured in Kilogram) - Desired Takeoff Weight (or mass) is the weight of the aircraft.
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).
Fuel Fraction - Fuel Fraction is the ratio between weight of fuel caried by a plane to the aircraft total take off weight.

STEP 1: Convert Input(s) to Base Unit

Fuel Weight to be Carried: 100000 Kilogram --> 100000 Kilogram No Conversion Required
Fuel Fraction: 0.4 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

DTW = FW/F_f --> 100000/0.4

Evaluating ... ...

DTW = 250000

STEP 3: Convert Result to Output's Unit

250000 Kilogram --> No Conversion Required

FINAL ANSWER

250000 Kilogram <-- Desired Takeoff Weight

(Calculation completed in 00.020 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!

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National Institute Of Technology (NIT), Hamirpur

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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 Optimum 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 Preliminary 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 = Harmonic Range-Range Increment of Aircraft

Takeoff Weight given Fuel Fraction Formula

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

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 Takeoff Weight given Fuel Fraction?

Takeoff Weight given Fuel Fraction calculator uses Desired Takeoff Weight = Fuel Weight to be Carried/Fuel Fraction to calculate the Desired Takeoff Weight, The Takeoff Weight given Fuel Fraction refers to the total weight of the aircraft, including all components and payloads, at the moment it lifts off the ground for flight, to calculate the takeoff weight of an aircraft given the fuel fraction, you'll need to consider the relationship between the fuel fraction, the empty weight fraction, and the total takeoff weight. Desired Takeoff Weight is denoted by DTW symbol.

How to calculate Takeoff Weight given Fuel Fraction using this online calculator? To use this online calculator for Takeoff Weight given Fuel Fraction, enter Fuel Weight to be Carried (FW) & Fuel Fraction (F_f) and hit the calculate button. Here is how the Takeoff Weight given Fuel Fraction calculation can be explained with given input values -> 400000 = 100000/0.4.

FAQ

What is Takeoff Weight given Fuel Fraction?

The Takeoff Weight given Fuel Fraction refers to the total weight of the aircraft, including all components and payloads, at the moment it lifts off the ground for flight, to calculate the takeoff weight of an aircraft given the fuel fraction, you'll need to consider the relationship between the fuel fraction, the empty weight fraction, and the total takeoff weight and is represented as DTW = FW/F_f or Desired Takeoff Weight = Fuel Weight to be Carried/Fuel Fraction. Fuel Weight to be Carried is defined as the total mass of the fuel to be carried (usually includes reserve fuel) & Fuel Fraction is the ratio between weight of fuel caried by a plane to the aircraft total take off weight.

How to calculate Takeoff Weight given Fuel Fraction?

The Takeoff Weight given Fuel Fraction refers to the total weight of the aircraft, including all components and payloads, at the moment it lifts off the ground for flight, to calculate the takeoff weight of an aircraft given the fuel fraction, you'll need to consider the relationship between the fuel fraction, the empty weight fraction, and the total takeoff weight is calculated using Desired Takeoff Weight = Fuel Weight to be Carried/Fuel Fraction. To calculate Takeoff Weight given Fuel Fraction, you need Fuel Weight to be Carried (FW) & Fuel Fraction (F_f). With our tool, you need to enter the respective value for Fuel Weight to be Carried & Fuel Fraction 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 Desired Takeoff Weight?

In this formula, Desired Takeoff Weight uses Fuel Weight to be Carried & Fuel Fraction. We can use 3 other way(s) to calculate the same, which is/are as follows -

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

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