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Preliminary Endurance for Jet Aircraft Calculator

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✖Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.ⓘ 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%

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

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Preliminary Endurance for Jet Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Preliminary 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
P_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

Preliminary Endurance of Aircraft - (Measured in Second) - Preliminary 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 refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.
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: 19.7 --> No Conversion Required
Weight of Aircraft at Beginning of Cruise Phase: 514 Kilogram --> 514 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

P_E = (LDmax_ratio*ln(W_i/W_f))/c --> (19.7*ln(514/350))/0.000166666666666667

Evaluating ... ...

P_E = 45423.0911168555

STEP 3: Convert Result to Output's Unit

45423.0911168555 Second --> No Conversion Required

FINAL ANSWER

45423.0911168555 ≈ 45423.09 Second <-- Preliminary Endurance of Aircraft

(Calculation completed in 00.020 seconds)

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< Preliminary Design Calculators

Optimum Range for Jet Aircraft in Cruising Phase

LaTeX 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)

Preliminary Take Off Weight Built-up for Manned Aircraft

LaTeX Go Desired Takeoff Weight = Payload Carried+Operating Empty Weight+Fuel Weight to be Carried+Crew Weight

Preliminary Take off Weight Built-Up for Manned Aircraft given Fuel and Empty Weight Fraction

LaTeX Go Desired Takeoff Weight = (Payload Carried+Crew Weight)/(1-Fuel Fraction-Empty Weight Fraction)

Fuel Fraction

LaTeX Go Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight

Preliminary Endurance for Jet Aircraft Formula

LaTeX Go

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 Preliminary 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 Preliminary 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. Preliminary Endurance of Aircraft is denoted by P_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 -> 45423.09 = (19.7*ln(514/350))/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 P_E = (LDmax_ratio*ln(W_i/W_f))/c or Preliminary 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 refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight, 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 Preliminary 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.

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