Preliminary Endurance for Jet Aircraft Calculator

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✖Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.ⓘ Maximum Lift to Drag Ratio of Aircraft [LDmax_ratio]			+10% -10%
✖Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.ⓘ Weight of Aircraft at Beginning of Cruise Phase [W_i]			+10% -10%
✖Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.ⓘ Weight of Aircraft at End of Cruise Phase [W_f]			+10% -10%
✖Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.ⓘ Power Specific Fuel Consumption [c]			+10% -10%

✖Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flight.ⓘ Preliminary Endurance for Jet Aircraft [E]

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Formula

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Preliminary Endurance for Jet Aircraft

Formula

`"E" = ("LDmax"_{"ratio"}*ln("W"_{"i"}/"W"_{"f"}))/"c"`

Example

`"45236.6s"=("30"*ln("450kg"/"350kg"))/"0.6kg/h/W"`

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Preliminary Endurance for Jet Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

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
E = (LDmax_ratio*ln(W_i/W_f))/c
This formula uses 1 Functions, 5 Variables

Functions Used

ln - The natural logarithm, also known as the logarithm to the base e, is the inverse function of the natural exponential function., ln(Number)

Variables Used

Endurance of Aircraft - (Measured in Second) - Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flight.
Maximum Lift to Drag Ratio of Aircraft - Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.
Weight of Aircraft at Beginning of Cruise Phase - (Measured in Kilogram) - Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.
Weight of Aircraft at End of Cruise Phase - (Measured in Kilogram) - Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.
Power Specific Fuel Consumption - (Measured in Kilogram per Second per Watt) - Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.

STEP 1: Convert Input(s) to Base Unit

Maximum Lift to Drag Ratio of Aircraft: 30 --> No Conversion Required
Weight of Aircraft at Beginning of Cruise Phase: 450 Kilogram --> 450 Kilogram No Conversion Required
Weight of Aircraft at End of Cruise Phase: 350 Kilogram --> 350 Kilogram No Conversion Required
Power Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

E = (LDmax_ratio*ln(W_i/W_f))/c --> (30*ln(450/350))/0.000166666666666667

Evaluating ... ...

E = 45236.597090563

STEP 3: Convert Result to Output's Unit

45236.597090563 Second --> No Conversion Required

FINAL ANSWER

45236.597090563 ≈ 45236.6 Second <-- Endurance of Aircraft

(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

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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

Preliminary Endurance for Jet Aircraft Formula

What do you mean by Endurance of Aircraft?

In aviation, endurance is the maximum length of time that an aircraft can spend in cruising flight. In other words, it is the amount of time an aircraft can stay in the air with one load of fuel. Endurance is different from range, which is a measure of distance flown. For example, a typical sailplane exhibits high endurance characteristics but poor range characteristics.
Endurance can factor into aviation design in a number of ways. Some aircraft, require high endurance characteristics as part of their mission profile (often referred to as loiter time). Endurance plays a prime factor in finding out the fuel fraction for an aircraft. Endurance, like range, is also related to fuel efficiency; fuel-efficient aircraft will tend to exhibit good endurance characteristics.

How to Calculate Preliminary Endurance for Jet Aircraft?

Preliminary Endurance for Jet Aircraft calculator uses 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 to calculate the Endurance of Aircraft, The Preliminary Endurance for Jet Aircraft formula gives you the maximum amount of time the jet aircraft can remain in flight on a single fuel load under normal operating conditions, this formula calculates the endurance of the aircraft by multiplying the maximum lift-to-drag ratio by the natural logarithm of the ratio of the aircraft's weight at the beginning and end of the cruising phase, and then dividing by the specific fuel consumption of the engines. Endurance of Aircraft is denoted by E symbol.

How to calculate Preliminary Endurance for Jet Aircraft using this online calculator? To use this online calculator for Preliminary Endurance for Jet Aircraft, enter Maximum Lift to Drag Ratio of Aircraft (LDmax_ratio), Weight of Aircraft at Beginning of Cruise Phase (W_i), Weight of Aircraft at End of Cruise Phase (W_f) & Power Specific Fuel Consumption (c) and hit the calculate button. Here is how the Preliminary Endurance for Jet Aircraft calculation can be explained with given input values -> 45236.6 = (30*ln(450/350))/0.000166666666666667.

FAQ

What is Preliminary Endurance for Jet Aircraft?

The Preliminary Endurance for Jet Aircraft formula gives you the maximum amount of time the jet aircraft can remain in flight on a single fuel load under normal operating conditions, this formula calculates the endurance of the aircraft by multiplying the maximum lift-to-drag ratio by the natural logarithm of the ratio of the aircraft's weight at the beginning and end of the cruising phase, and then dividing by the specific fuel consumption of the engines and is represented as E = (LDmax_ratio*ln(W_i/W_f))/c or 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 to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value, Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission, Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan & Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.

How to calculate Preliminary Endurance for Jet Aircraft?

The Preliminary Endurance for Jet Aircraft formula gives you the maximum amount of time the jet aircraft can remain in flight on a single fuel load under normal operating conditions, this formula calculates the endurance of the aircraft by multiplying the maximum lift-to-drag ratio by the natural logarithm of the ratio of the aircraft's weight at the beginning and end of the cruising phase, and then dividing by the specific fuel consumption of the engines is calculated using 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. To calculate Preliminary Endurance for Jet Aircraft, you need Maximum Lift to Drag Ratio of Aircraft (LDmax_ratio), Weight of Aircraft at Beginning of Cruise Phase (W_i), Weight of Aircraft at End of Cruise Phase (W_f) & Power Specific Fuel Consumption (c). With our tool, you need to enter the respective value for Maximum Lift to Drag Ratio of Aircraft, Weight of Aircraft at Beginning of Cruise Phase, Weight of Aircraft at End of Cruise Phase & Power Specific Fuel Consumption 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 Endurance of Aircraft?

In this formula, Endurance of Aircraft uses Maximum Lift to Drag Ratio of Aircraft, Weight of Aircraft at Beginning of Cruise Phase, Weight of Aircraft at End of Cruise Phase & Power Specific Fuel Consumption. We can use 1 other way(s) to calculate the same, which is/are as follows -

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)

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