Fuel Fraction given Takeoff Weight and Empty Weight Fraction Solution

STEP 0: Pre-Calculation Summary
Formula Used
Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight
Ff = 1-Ef-(PYL+Wc)/DTW
This formula uses 5 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.
Empty Weight Fraction - Empty Weight Fraction is the ration of Operating Empty Weight to Desired Takeoff Weight.
Payload Carried - (Measured in Kilogram) - Payload Carried (passengers and cargo) is the object or the entity which is being carried by an aircraft or a launch vehicle.
Crew Weight - (Measured in Kilogram) - Crew Weight is the weight of staff which are required for the functioning of the plane. It contains the weight of Pilots, flight engineer, navigation pilot and airplane staff to serve the passengers.
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
Empty Weight Fraction: 0.7 --> No Conversion Required
Payload Carried: 12400 Kilogram --> 12400 Kilogram No Conversion Required
Crew Weight: 180 Kilogram --> 180 Kilogram No Conversion Required
Desired Takeoff Weight: 250000 Kilogram --> 250000 Kilogram No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Ff = 1-Ef-(PYL+Wc)/DTW --> 1-0.7-(12400+180)/250000
Evaluating ... ...
Ff = 0.24968
STEP 3: Convert Result to Output's Unit
0.24968 --> No Conversion Required
FINAL ANSWER
0.24968 <-- Fuel Fraction
(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
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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 given Takeoff Weight and Empty Weight Fraction Formula

Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight
Ff = 1-Ef-(PYL+Wc)/DTW

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 given Takeoff Weight and Empty Weight Fraction?

Fuel Fraction given Takeoff Weight and Empty Weight Fraction calculator uses Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight to calculate the Fuel Fraction, The Fuel Fraction given Takeoff Weight and Empty Weight Fraction formula is to calculate the Fuel Fraction if Takeoff Weight, Empty Weight Fraction, Payload Weight and Crew Weight is given. Fuel Fraction is denoted by Ff symbol.

How to calculate Fuel Fraction given Takeoff Weight and Empty Weight Fraction using this online calculator? To use this online calculator for Fuel Fraction given Takeoff Weight and Empty Weight Fraction, enter Empty Weight Fraction (Ef), Payload Carried (PYL), Crew Weight (Wc) & Desired Takeoff Weight (DTW) and hit the calculate button. Here is how the Fuel Fraction given Takeoff Weight and Empty Weight Fraction calculation can be explained with given input values -> 0.24968 = 1-0.7-(12400+180)/250000.

FAQ

What is Fuel Fraction given Takeoff Weight and Empty Weight Fraction?
The Fuel Fraction given Takeoff Weight and Empty Weight Fraction formula is to calculate the Fuel Fraction if Takeoff Weight, Empty Weight Fraction, Payload Weight and Crew Weight is given and is represented as Ff = 1-Ef-(PYL+Wc)/DTW or Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight. Empty Weight Fraction is the ration of Operating Empty Weight to Desired Takeoff Weight, Payload Carried (passengers and cargo) is the object or the entity which is being carried by an aircraft or a launch vehicle, Crew Weight is the weight of staff which are required for the functioning of the plane. It contains the weight of Pilots, flight engineer, navigation pilot and airplane staff to serve the passengers & Desired Takeoff Weight (or mass) is the weight of the aircraft.
How to calculate Fuel Fraction given Takeoff Weight and Empty Weight Fraction?
The Fuel Fraction given Takeoff Weight and Empty Weight Fraction formula is to calculate the Fuel Fraction if Takeoff Weight, Empty Weight Fraction, Payload Weight and Crew Weight is given is calculated using Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight. To calculate Fuel Fraction given Takeoff Weight and Empty Weight Fraction, you need Empty Weight Fraction (Ef), Payload Carried (PYL), Crew Weight (Wc) & Desired Takeoff Weight (DTW). With our tool, you need to enter the respective value for Empty Weight Fraction, Payload Carried, Crew Weight & 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 Empty Weight Fraction, Payload Carried, Crew Weight & Desired Takeoff Weight. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight
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