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

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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. Check FAQs

LDEmax ratio prop = \frac{E \cdot V Emax \cdot c}{η \cdot \ln (\frac{W L,beg}{W L,end})}

LDEmax_{ratio prop} - Lift to Drag Ratio at Maximum Endurance Prop?E - Endurance of Aircraft?V_Emax - Velocity for Maximum Endurance?c - Specific Fuel Consumption?η - Propeller Efficiency?W_L,beg - Weight at Start of Loiter Phase?W_L,end - Weight at End of Loiter Phase?

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

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Here is how the Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft equation looks like with Values.

Here is how the Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft equation looks like with Units.

Here is how the Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft equation looks like.

85.0491 = \frac{452.0581 \cdot 15.6 \cdot 0.6}{0.93 \cdot \ln (\frac{400}{394.1})}

85.0491 = \frac{452.0581s \cdot 15.6m/s \cdot 0.6kg/h/W}{0.93 \cdot \ln (\frac{400kg}{394.1kg})}

85.0491 = \frac{452.0581 \cdot 15.6 \cdot 0.6}{0.93 \cdot \ln (\frac{400}{394.1})}

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

Follow our step by step solution on how to calculate Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft?

FIRST Step Consider the formula

LDEmax ratio prop = \frac{E \cdot V Emax \cdot c}{η \cdot \ln (\frac{W L,beg}{W L,end})}

Next Step Substitute values of Variables

∴

LDEmax ratio prop = \frac{452.0581s \cdot 15.6m/s \cdot 0.6kg/h/W}{0.93 \cdot \ln (\frac{400kg}{394.1kg})}

Next Step Convert Units

∴

LDEmax ratio prop = \frac{452.0581s \cdot 15.6m/s \cdot 0.0002kg/s/W}{0.93 \cdot \ln (\frac{400kg}{394.1kg})}

Next Step Prepare to Evaluate

∴

LDEmax ratio prop = \frac{452.0581 \cdot 15.6 \cdot 0.0002}{0.93 \cdot \ln (\frac{400}{394.1})}

Next Step Evaluate

∴

LDEmax ratio prop = 85.0491254188244

LAST Step Rounding Answer

∴

LDEmax ratio prop = 85.0491

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

Variables

Functions

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.

Symbol: LDEmax_{ratio prop}

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift to Drag Ratio at Maximum Endurance Prop

Endurance of Aircraft

Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.

Symbol: E

Measurement: TimeUnit: s

Note: Value should be greater than 0.

Formulas to find Endurance of Aircraft

Velocity for Maximum Endurance

Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.

Symbol: V_Emax

Measurement: SpeedUnit: m/s

Note: Value should be greater than 0.

Formulas to find Velocity for Maximum Endurance

Specific Fuel Consumption

Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.

Symbol: c

Measurement: Specific Fuel ConsumptionUnit: kg/h/W

Note: Value should be greater than 0.

Formulas to find Specific Fuel Consumption

Propeller Efficiency

Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).

Symbol: η

Measurement: NAUnit: Unitless

Note: Value should be less than 1.

Formulas to find Propeller Efficiency

Weight at Start of Loiter Phase

Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase.

Symbol: W_L,beg

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight at Start of Loiter Phase

Weight at End of 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.

Symbol: W_L,end

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight at End of Loiter Phase

The natural logarithm, also known as the logarithm to the base e, is the inverse function of the natural exponential function.

Syntax: ln(Number)

Other formulas in Propeller Driven Airplane category

Go Range of Propeller-Driven Airplane

R prop = (\frac{η}{c}) \cdot (\frac{C L}{C D}) \cdot (\ln (\frac{W 0}{W 1}))

Go Propeller Efficiency for given Range of Propeller-Driven Airplane

η = R prop \cdot c \cdot \frac{C D}{C L \cdot \ln (\frac{W 0}{W 1})}

How to Evaluate 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 evaluator 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 evaluate 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 evaluate Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft using this online evaluator? To use this online evaluator 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.

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

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

The formula of Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft is expressed as 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)). Here is an example- 85.04913 = (452.0581*15.6*0.000166666666666667)/(0.93*ln(400/394.1)).

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

With 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) we can find Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft using the formula - 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)). This formula also uses Natural Logarithm (ln) function(s).

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

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

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

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

Other formulas in Propeller Driven Airplane category

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

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

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