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/Ff
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: 1100 Kilogram --> 1100 Kilogram No Conversion Required
Fuel Fraction: 0.25 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
DTW = FW/Ff --> 1100/0.25
Evaluating ... ...
DTW = 4400
STEP 3: Convert Result to Output's Unit
4400 Kilogram --> No Conversion Required
FINAL ANSWER
4400 Kilogram <-- Desired Takeoff Weight
(Calculation completed in 00.004 seconds)

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 Anshika Arya
National Institute Of Technology (NIT), Hamirpur
Anshika Arya has verified this Calculator and 2500+ more calculators!

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

Takeoff Weight given Fuel Fraction Formula

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

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 formula is calculation of Take Off Weight when Fuel Weight and Fuel Fraction are given. 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 (Ff) and hit the calculate button. Here is how the Takeoff Weight given Fuel Fraction calculation can be explained with given input values -> 4400 = 1100/0.25.

FAQ

What is Takeoff Weight given Fuel Fraction?
The Takeoff Weight given Fuel Fraction formula is calculation of Take Off Weight when Fuel Weight and Fuel Fraction are given and is represented as DTW = FW/Ff 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 formula is calculation of Take Off Weight when Fuel Weight and Fuel Fraction are given 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 (Ff). 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
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!