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Lift-to-Drag ratio for given Range of Propeller-Driven Airplane Formula

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The Lift-to-Drag Ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air. Check FAQs

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

LD - Lift-to-Drag Ratio?c - Specific Fuel Consumption?R_prop - Range of Propeller Aircraft?η - Propeller Efficiency?W₀ - Gross Weight?W₁ - Weight without Fuel?

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane Example

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Here is how the Lift-to-Drag ratio for given Range of Propeller-Driven Airplane equation looks like with Values.

Here is how the Lift-to-Drag ratio for given Range of Propeller-Driven Airplane equation looks like with Units.

Here is how the Lift-to-Drag ratio for given Range of Propeller-Driven Airplane equation looks like.

2.5 = 0.6 \cdot \frac{7126.017}{0.93 \cdot \ln (\frac{5000}{3000})}

2.5 = 0.6kg/h/W \cdot \frac{7126.017m}{0.93 \cdot \ln (\frac{5000kg}{3000kg})}

2.5 = 0.6 \cdot \frac{7126.017}{0.93 \cdot \ln (\frac{5000}{3000})}

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Lift-to-Drag ratio for given Range of Propeller-Driven Airplane Solution

Follow our step by step solution on how to calculate Lift-to-Drag ratio for given Range of Propeller-Driven Airplane?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

LD = 0.6kg/h/W \cdot \frac{7126.017m}{0.93 \cdot \ln (\frac{5000kg}{3000kg})}

Next Step Convert Units

∴

LD = 0.0002kg/s/W \cdot \frac{7126.017m}{0.93 \cdot \ln (\frac{5000kg}{3000kg})}

Next Step Prepare to Evaluate

∴

LD = 0.0002 \cdot \frac{7126.017}{0.93 \cdot \ln (\frac{5000}{3000})}

Next Step Evaluate

∴

LD = 2.49999984158909

LAST Step Rounding Answer

∴

LD = 2.5

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane Formula Elements

Variables

Functions

Lift-to-Drag Ratio

The Lift-to-Drag Ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air.

Symbol: LD

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift-to-Drag Ratio

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

Range of Propeller Aircraft

Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.

Symbol: R_prop

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Range of Propeller Aircraft

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

Gross Weight

The Gross Weight of the airplane is the weight with full fuel and payload.

Symbol: W₀

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Gross Weight

Weight without Fuel

Weight without Fuel is the total weight of the airplane without fuel.

Symbol: W₁

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight without Fuel

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})}

Go Specific Fuel Consumption for given Range of Propeller-Driven Airplane

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

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

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

How to Evaluate Lift-to-Drag ratio for given Range of Propeller-Driven Airplane?

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane evaluator uses Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel)) to evaluate the Lift-to-Drag Ratio, Lift-to-Drag ratio for given Range of Propeller-Driven Airplane is a measure of the ratio of an aircraft's lift to its drag, which is essential in determining the efficiency of an airplane's propeller-driven system, taking into account factors such as specific fuel consumption, range, propeller efficiency, and weight. Lift-to-Drag Ratio is denoted by LD symbol.

How to evaluate Lift-to-Drag ratio for given Range of Propeller-Driven Airplane using this online evaluator? To use this online evaluator for Lift-to-Drag ratio for given Range of Propeller-Driven Airplane, enter Specific Fuel Consumption (c), Range of Propeller Aircraft (R_prop), Propeller Efficiency (η), Gross Weight (W₀) & Weight without Fuel (W₁) and hit the calculate button.

FAQs on Lift-to-Drag ratio for given Range of Propeller-Driven Airplane

What is the formula to find Lift-to-Drag ratio for given Range of Propeller-Driven Airplane?

The formula of Lift-to-Drag ratio for given Range of Propeller-Driven Airplane is expressed as Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel)). Here is an example- 2.499994 = 0.000166666666666667*7126.017/(0.93*ln(5000/3000)).

How to calculate Lift-to-Drag ratio for given Range of Propeller-Driven Airplane?

With Specific Fuel Consumption (c), Range of Propeller Aircraft (R_prop), Propeller Efficiency (η), Gross Weight (W₀) & Weight without Fuel (W₁) we can find Lift-to-Drag ratio for given Range of Propeller-Driven Airplane using the formula - Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel)). This formula also uses Natural Logarithm Function function(s).

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Lift-to-Drag ratio for given Range of Propeller-Driven Airplane Formula

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane Example

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane Solution

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane Formula Elements

Other formulas in Propeller Driven Airplane category

How to Evaluate Lift-to-Drag ratio for given Range of Propeller-Driven Airplane?

FAQs on Lift-to-Drag ratio for given Range of Propeller-Driven Airplane

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