Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven 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%
✖Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.ⓘ Velocity for Maximum Endurance [V_Emax]			+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%
✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+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%

✖Lift to Drag Ratio at Maximum Endurance Prop is the ratio of lift to drag at which the plane can fly (or loiter) for maximum time.ⓘ Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft [LDEmax_{ratio prop}]

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Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift to Drag Ratio at Maximum Endurance Prop = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))
LDEmax_{ratio prop} = (E*V_Emax*c)/(η*ln(W_L,beg/W_L,end))
This formula uses 1 Functions, 7 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

Lift to Drag Ratio at Maximum Endurance Prop - Lift to Drag Ratio at Maximum Endurance Prop is the ratio of lift to drag at which the plane can fly (or loiter) for maximum time.
Endurance of Aircraft - (Measured in Second) - Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.
Velocity for Maximum Endurance - (Measured in Meter per Second) - Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.
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.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
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
Velocity for Maximum Endurance: 15.6 Meter per Second --> 15.6 Meter per Second No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Propeller Efficiency: 0.93 --> No Conversion Required
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

LDEmax_{ratio prop} = (E*V_Emax*c)/(η*ln(W_L,beg/W_L,end)) --> (452.0581*15.6*0.000166666666666667)/(0.93*ln(400/394.1))

Evaluating ... ...

LDEmax_{ratio prop} = 85.0491254188244

STEP 3: Convert Result to Output's Unit

85.0491254188244 --> No Conversion Required

FINAL ANSWER

85.0491254188244 ≈ 85.04913 <-- Lift to Drag Ratio at Maximum Endurance Prop

(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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Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore

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< Propeller Driven Airplane Calculators

Specific Fuel Consumption for given Range of Propeller-Driven Airplane

LaTeX Go Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel))

Range of Propeller-Driven Airplane

LaTeX Go Range of Propeller Aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel))

Propeller Efficiency for given Range of Propeller-Driven Airplane

LaTeX Go Propeller Efficiency = Range of Propeller Aircraft*Specific Fuel Consumption*Drag Coefficient/(Lift Coefficient*ln(Gross Weight/Weight without Fuel))

Range of Propeller-Driven Airplane for given lift-to-drag ratio

LaTeX Go Range of Propeller Aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel))

Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven 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 a 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.

What is Lift to Drag ratio?

The lift-to-drag ratio (or L/D ratio) is the lift generated by an aerodynamic body such as an airfoil or aircraft, divided by the aerodynamic drag caused by moving through air. It describes the aerodynamic efficiency under given flight conditions. The L/D ratio for any given body will vary according to these flight conditions.
For an airfoil wing or powered aircraft, the L/D is specified when in straight and level flight. For a glider, it determines the glide ratio, of distance travelled against loss of height.
The term is calculated for any particular airspeed by measuring the lift generated, then dividing by the drag at that speed.
And the lift to drag ratio when the plane can fly for the maximum time is known as lift to drag ratio for maximum Endurance.

How to Calculate Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft?

Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft calculator uses Lift to Drag Ratio at Maximum Endurance Prop = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)) to calculate the Lift to Drag Ratio at Maximum Endurance Prop, Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft is a measure of the optimal ratio of lift to drag forces that enables an aircraft to achieve maximum endurance, given the preliminary endurance and propeller-driven aircraft specifications. Lift to Drag Ratio at Maximum Endurance Prop is denoted by LDEmax_{ratio prop} symbol.

How to calculate Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft using this online calculator? To use this online calculator for Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft, enter Endurance of Aircraft (E), Velocity for Maximum Endurance (V_Emax), Specific Fuel Consumption (c), Propeller Efficiency (η), 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 Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft calculation can be explained with given input values -> 85.04913 = (452.0581*15.6*0.000166666666666667)/(0.93*ln(400/394.1)).

FAQ

What is Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft?

Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft is a measure of the optimal ratio of lift to drag forces that enables an aircraft to achieve maximum endurance, given the preliminary endurance and propeller-driven aircraft specifications and is represented as LDEmax_{ratio prop} = (E*V_Emax*c)/(η*ln(W_L,beg/W_L,end)) or Lift to Drag Ratio at Maximum Endurance Prop = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Propeller Efficiency*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, Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance, Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), 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 Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft?

Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft is a measure of the optimal ratio of lift to drag forces that enables an aircraft to achieve maximum endurance, given the preliminary endurance and propeller-driven aircraft specifications is calculated using Lift to Drag Ratio at Maximum Endurance Prop = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)). To calculate Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft, you need Endurance of Aircraft (E), Velocity for Maximum Endurance (V_Emax), Specific Fuel Consumption (c), Propeller Efficiency (η), 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, Velocity for Maximum Endurance, Specific Fuel Consumption, Propeller Efficiency, 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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