Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft Calculator

✖Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.ⓘ Endurance of Aircraft [E]			+10% -10%
✖Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.ⓘ Specific Fuel Consumption [c]			+10% -10%
✖Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase.ⓘ Weight at Start of Loiter Phase [W_L,beg]			+10% -10%
✖The Weight at End of Loiter Phase refers to the aircraft's mass after completing a period of flying at a predetermined location or holding pattern.ⓘ Weight at End of Loiter Phase [W_L,end]			+10% -10%

✖The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.ⓘ Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft [LDmax_ratio]

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Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Maximum Lift-to-Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)
LDmax_ratio = (E*c)/ln(W_L,beg/W_L,end)
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

Maximum Lift-to-Drag Ratio - The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.
Endurance of Aircraft - (Measured in Second) - Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.
Specific Fuel Consumption - (Measured in Kilogram per Second per Watt) - Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.
Weight at Start of Loiter Phase - (Measured in Kilogram) - Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase.
Weight at End of Loiter Phase - (Measured in Kilogram) - The Weight at End of Loiter Phase refers to the aircraft's mass after completing a period of flying at a predetermined location or holding pattern.

STEP 1: Convert Input(s) to Base Unit

Endurance of Aircraft: 452.0581 Second --> 452.0581 Second No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Weight at Start of Loiter Phase: 400 Kilogram --> 400 Kilogram No Conversion Required
Weight at End of Loiter Phase: 394.1 Kilogram --> 394.1 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

LDmax_ratio = (E*c)/ln(W_L,beg/W_L,end) --> (452.0581*0.000166666666666667)/ln(400/394.1)

Evaluating ... ...

LDmax_ratio = 5.0702363230453

STEP 3: Convert Result to Output's Unit

5.0702363230453 --> No Conversion Required

FINAL ANSWER

5.0702363230453 ≈ 5.070236 <-- Maximum Lift-to-Drag Ratio

(Calculation completed in 00.004 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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< Jet Airplane Calculators

Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

LaTeX Go Thrust-Specific Fuel Consumption = Lift Coefficient*(ln(Gross Weight/Weight without Fuel))/(Drag Coefficient*Endurance of Aircraft)

Endurance of Jet Airplane

LaTeX Go Endurance of Aircraft = Lift Coefficient*(ln(Gross Weight/Weight without Fuel))/(Drag Coefficient*Thrust-Specific Fuel Consumption)

Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag Ratio of Jet Airplane

LaTeX Go Thrust-Specific Fuel Consumption = (1/Endurance of Aircraft)*Lift-to-Drag Ratio*ln(Gross Weight/Weight without Fuel)

Endurance for given Lift-to-Drag Ratio of Jet Airplane

LaTeX Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*Lift-to-Drag Ratio*ln(Gross Weight/Weight without Fuel)

Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft Formula

LaTeX Go

Maximum Lift-to-Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)
LDmax_ratio = (E*c)/ln(W_L,beg/W_L,end)

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 Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft?

Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft calculator uses Maximum Lift-to-Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase) to calculate the Maximum Lift-to-Drag Ratio, Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft is a measure of maximum lift to drag ratio of a jet aircraft during endurance flights, calculated by considering the aircraft's preliminary endurance, specific fuel consumption and weight changes during loiter, this enabling designers to optimize aircraft performance and fuel efficiency. Maximum Lift-to-Drag Ratio is denoted by LDmax_ratio symbol.

How to calculate Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft using this online calculator? To use this online calculator for Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft, enter Endurance of Aircraft (E), Specific Fuel Consumption (c), Weight at Start of Loiter Phase (W_L,beg) & Weight at End of Loiter Phase (W_L,end) and hit the calculate button. Here is how the Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft calculation can be explained with given input values -> 5.069585 = (452.0581*0.000166666666666667)/ln(400/394.1).

FAQ

What is Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft?

Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft is a measure of maximum lift to drag ratio of a jet aircraft during endurance flights, calculated by considering the aircraft's preliminary endurance, specific fuel consumption and weight changes during loiter, this enabling designers to optimize aircraft performance and fuel efficiency and is represented as LDmax_ratio = (E*c)/ln(W_L,beg/W_L,end) or Maximum Lift-to-Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase). Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight, Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase & The Weight at End of Loiter Phase refers to the aircraft's mass after completing a period of flying at a predetermined location or holding pattern.

How to calculate Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft?

Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft is a measure of maximum lift to drag ratio of a jet aircraft during endurance flights, calculated by considering the aircraft's preliminary endurance, specific fuel consumption and weight changes during loiter, this enabling designers to optimize aircraft performance and fuel efficiency is calculated using Maximum Lift-to-Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase). To calculate Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft, you need Endurance of Aircraft (E), Specific Fuel Consumption (c), Weight at Start of Loiter Phase (W_L,beg) & Weight at End of Loiter Phase (W_L,end). With our tool, you need to enter the respective value for Endurance of Aircraft, Specific Fuel Consumption, Weight at Start of Loiter Phase & Weight at End of Loiter Phase 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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