Empty Weight given Takeoff Weight Solution

STEP 0: Pre-Calculation Summary
Formula Used
Operating Empty Weight = Desired Takeoff Weight-Fuel Weight to be Carried-Payload Carried-Crew Weight
OEW = DTW-FW-PYL-Wc
This formula uses 5 Variables
Variables Used
Operating Empty Weight - (Measured in Kilogram) - Operating Empty Weight of the Aircraft is the weight of the aircraft without including passengers, baggage, or fuel.
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).
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.
STEP 1: Convert Input(s) to Base Unit
Desired Takeoff Weight: 250000 Kilogram --> 250000 Kilogram No Conversion Required
Fuel Weight to be Carried: 1100 Kilogram --> 1100 Kilogram No Conversion Required
Payload Carried: 12400 Kilogram --> 12400 Kilogram No Conversion Required
Crew Weight: 180 Kilogram --> 180 Kilogram No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
OEW = DTW-FW-PYL-Wc --> 250000-1100-12400-180
Evaluating ... ...
OEW = 236320
STEP 3: Convert Result to Output's Unit
236320 Kilogram --> No Conversion Required
FINAL ANSWER
236320 Kilogram <-- Operating Empty Weight
(Calculation completed in 00.020 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

Empty Weight given Takeoff Weight Formula

Operating Empty Weight = Desired Takeoff Weight-Fuel Weight to be Carried-Payload Carried-Crew Weight
OEW = DTW-FW-PYL-Wc

What is empty weight of an aircraft?

The empty weight of an aircraft is the weight of the aircraft without including passengers, baggage, or fuel. Standard empty weight usually includes unusable fuel, full operating fluids, and full engine oil.

How to Calculate Empty Weight given Takeoff Weight?

Empty Weight given Takeoff Weight calculator uses Operating Empty Weight = Desired Takeoff Weight-Fuel Weight to be Carried-Payload Carried-Crew Weight to calculate the Operating Empty Weight, The Empty Weight given Takeoff Weight formula is the weight of the aircraft without including passengers, baggage, or fuel. Standard empty weight usually includes unusable fuel, full operating fluids, and full engine oil. Operating Empty Weight is denoted by OEW symbol.

How to calculate Empty Weight given Takeoff Weight using this online calculator? To use this online calculator for Empty Weight given Takeoff Weight, enter Desired Takeoff Weight (DTW), Fuel Weight to be Carried (FW), Payload Carried (PYL) & Crew Weight (Wc) and hit the calculate button. Here is how the Empty Weight given Takeoff Weight calculation can be explained with given input values -> 236320 = 250000-1100-12400-180.

FAQ

What is Empty Weight given Takeoff Weight?
The Empty Weight given Takeoff Weight formula is the weight of the aircraft without including passengers, baggage, or fuel. Standard empty weight usually includes unusable fuel, full operating fluids, and full engine oil and is represented as OEW = DTW-FW-PYL-Wc or Operating Empty Weight = Desired Takeoff Weight-Fuel Weight to be Carried-Payload Carried-Crew Weight. Desired Takeoff Weight (or mass) is the weight of the aircraft, Fuel Weight to be Carried is defined as the total mass of the fuel to be carried (usually includes reserve fuel), 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.
How to calculate Empty Weight given Takeoff Weight?
The Empty Weight given Takeoff Weight formula is the weight of the aircraft without including passengers, baggage, or fuel. Standard empty weight usually includes unusable fuel, full operating fluids, and full engine oil is calculated using Operating Empty Weight = Desired Takeoff Weight-Fuel Weight to be Carried-Payload Carried-Crew Weight. To calculate Empty Weight given Takeoff Weight, you need Desired Takeoff Weight (DTW), Fuel Weight to be Carried (FW), Payload Carried (PYL) & Crew Weight (Wc). With our tool, you need to enter the respective value for Desired Takeoff Weight, Fuel Weight to be Carried, Payload Carried & Crew 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 Operating Empty Weight?
In this formula, Operating Empty Weight uses Desired Takeoff Weight, Fuel Weight to be Carried, Payload Carried & Crew Weight. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Operating Empty Weight = Empty Weight Fraction*Desired Takeoff Weight
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