FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft Formula

GoMaximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft Formula

Fx Copy

LaTeX Copy

The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve. Check FAQs

LDmax ratio = \frac{R prop \cdot c}{η \cdot \ln (\frac{W i}{W f})}

LDmax_ratio - Maximum Lift-to-Drag Ratio?R_prop - Range of Propeller Aircraft?c - Specific Fuel Consumption?η - Propeller Efficiency?W_i - Weight at Start of Cruise Phase?W_f - Weight at End of Cruise Phase?

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft Example

With values

With units

Only example

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

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

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

5.0815 = \frac{7126.017 \cdot 0.6}{0.93 \cdot \ln (\frac{450}{350})}

5.0815 = \frac{7126.017m \cdot 0.6kg/h/W}{0.93 \cdot \ln (\frac{450kg}{350kg})}

5.0815 = \frac{7126.017 \cdot 0.6}{0.93 \cdot \ln (\frac{450}{350})}

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aircraft Mechanics » fx Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft Solution

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

FIRST Step Consider the formula

LDmax ratio = \frac{R prop \cdot c}{η \cdot \ln (\frac{W i}{W f})}

Next Step Substitute values of Variables

∴

LDmax ratio = \frac{7126.017m \cdot 0.6kg/h/W}{0.93 \cdot \ln (\frac{450kg}{350kg})}

Next Step Convert Units

∴

LDmax ratio = \frac{7126.017m \cdot 0.0002kg/s/W}{0.93 \cdot \ln (\frac{450kg}{350kg})}

Next Step Prepare to Evaluate

∴

LDmax ratio = \frac{7126.017 \cdot 0.0002}{0.93 \cdot \ln (\frac{450}{350})}

Next Step Evaluate

∴

LDmax ratio = 5.08153864157449

LAST Step Rounding Answer

∴

LDmax ratio = 5.0815

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft Formula Elements

Variables

Functions

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.

Symbol: LDmax_ratio

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Maximum Lift-to-Drag Ratio

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

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 Cruise Phase

Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.

Symbol: W_i

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight at Start of Cruise Phase

Weight at End of Cruise Phase

Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

Symbol: W_f

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight at End of Cruise 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 to find Maximum Lift-to-Drag Ratio

Go Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft

LDmax ratio = \frac{LDEmax ratio}{0.866}

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 Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft?

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft evaluator uses Maximum Lift-to-Drag Ratio = (Range of Propeller Aircraft*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase)) to evaluate the Maximum Lift-to-Drag Ratio, Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft is a measure of the optimal ratio of lift to drag for a propeller-driven aircraft, considering the range of the aircraft, specific fuel consumption, propeller efficiency, and weight changes during cruise, this ratio is crucial in aircraft design as it directly affects fuel efficiency, range, and overall performance. Maximum Lift-to-Drag Ratio is denoted by LDmax_ratio symbol.

How to evaluate Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft using this online evaluator? To use this online evaluator for Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft, enter Range of Propeller Aircraft (R_prop), Specific Fuel Consumption (c), Propeller Efficiency (η), Weight at Start of Cruise Phase (W_i) & Weight at End of Cruise Phase (W_f) and hit the calculate button.

FAQs on Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft

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

The formula of Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft is expressed as Maximum Lift-to-Drag Ratio = (Range of Propeller Aircraft*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase)). Here is an example- 5.081539 = (7126.017*0.000166666666666667)/(0.93*ln(450/350)).

How to calculate Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft?

With Range of Propeller Aircraft (R_prop), Specific Fuel Consumption (c), Propeller Efficiency (η), Weight at Start of Cruise Phase (W_i) & Weight at End of Cruise Phase (W_f) we can find Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft using the formula - Maximum Lift-to-Drag Ratio = (Range of Propeller Aircraft*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase)). This formula also uses Natural Logarithm (ln) function(s).

What are the other ways to Calculate Maximum Lift-to-Drag Ratio?

Here are the different ways to Calculate Maximum Lift-to-Drag Ratio-

Maximum Lift-to-Drag Ratio=Lift to Drag Ratio at Maximum Endurance/0.866

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft Formula

​GoMaximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft Formula

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft Example

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft Solution

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft Formula Elements

Other Formulas to find Maximum Lift-to-Drag Ratio

Other formulas in Propeller Driven Airplane category

How to Evaluate Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft?

FAQs on Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft

Variable Name

GoMaximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft Formula