Payload Weight given Takeoff Weight Solution

STEP 0: Pre-Calculation Summary
Formula Used
Payload Carried = Desired Takeoff Weight-Operating Empty Weight-Crew Weight-Fuel Weight to be Carried
PYL = DTW-OEW-Wc-FW
This formula uses 5 Variables
Variables Used
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.
Desired Takeoff Weight - (Measured in Kilogram) - Desired Takeoff Weight (or mass) is the weight of the aircraft.
Operating Empty Weight - (Measured in Kilogram) - Operating Empty Weight of the Aircraft is the weight of the aircraft without including passengers, baggage, or fuel.
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.
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).
STEP 1: Convert Input(s) to Base Unit
Desired Takeoff Weight: 250000 Kilogram --> 250000 Kilogram No Conversion Required
Operating Empty Weight: 10000 Kilogram --> 10000 Kilogram No Conversion Required
Crew Weight: 180 Kilogram --> 180 Kilogram No Conversion Required
Fuel Weight to be Carried: 1100 Kilogram --> 1100 Kilogram No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
PYL = DTW-OEW-Wc-FW --> 250000-10000-180-1100
Evaluating ... ...
PYL = 238720
STEP 3: Convert Result to Output's Unit
238720 Kilogram --> No Conversion Required
FINAL ANSWER
238720 Kilogram <-- Payload Carried
(Calculation completed in 00.004 seconds)

Credits

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Created by Vedant Chitte
All India Shri Shivaji Memorials Society's ,College of Engineering (AISSMS COE PUNE), Pune
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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 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

Payload Weight given Takeoff Weight Formula

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

What is Payload Weight?

Payload is the object or the entity which is being carried by aircraft or launch vehicle. Sometimes payload also refers to the carrying capacity of an aircraft or launch vehicle, usually measured in terms of weight. Depending on the nature of the flight or mission, the payload of a vehicle may include cargo, passengers, munitions, scientific instruments or experiments, or other equipment. Extra fuel, when optionally carried, is also considered part of the payload.
In a commercial context (i.e., an airline or air freight carrier), the payload may refer only to revenue-generating cargo or paying passengers. A payload of ordnance carried by a combat aircraft is sometimes alternatively referred to as the aircraft's war load.

How to Calculate Payload Weight given Takeoff Weight?

Payload Weight given Takeoff Weight calculator uses Payload Carried = Desired Takeoff Weight-Operating Empty Weight-Crew Weight-Fuel Weight to be Carried to calculate the Payload Carried, The Payload Weight given Takeoff Weight formula is defined as the weight of the passengers, luggage, or a thing carried by aircraft. Payload Carried is denoted by PYL symbol.

How to calculate Payload Weight given Takeoff Weight using this online calculator? To use this online calculator for Payload Weight given Takeoff Weight, enter Desired Takeoff Weight (DTW), Operating Empty Weight (OEW), Crew Weight (Wc) & Fuel Weight to be Carried (FW) and hit the calculate button. Here is how the Payload Weight given Takeoff Weight calculation can be explained with given input values -> 0.23872 = 250000-10000-180-1100.

FAQ

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