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

✖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%
✖Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Range of Propeller Aircraft [R_prop]			+10% -10%
✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+10% -10%
✖The Gross Weight of the airplane is the weight with full fuel and payload.ⓘ Gross Weight [W₀]			+10% -10%
✖Weight without Fuel is the total weight of the airplane without fuel.ⓘ Weight without Fuel [W₁]			+10% -10%

✖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.ⓘ Lift-to-Drag ratio for given Range of Propeller-Driven Airplane [LD]

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

Formula

`"LD" = "c"*"R"_{"prop"}/("η"*ln("W"_{"0"}/"W"_{"1"}))`

Example

`"2.5"="0.6kg/h/W"*"7126.017m"/("0.93"*ln("5000kg"/"3000kg"))`

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

STEP 0: Pre-Calculation Summary

Formula Used

Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel))
LD = c*R_prop/(η*ln(W₀/W₁))
This formula uses 1 Functions, 6 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 - 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.
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.
Range of Propeller Aircraft - (Measured in Meter) - Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
Gross Weight - (Measured in Kilogram) - The Gross Weight of the airplane is the weight with full fuel and payload.
Weight without Fuel - (Measured in Kilogram) - Weight without Fuel is the total weight of the airplane without fuel.

STEP 1: Convert Input(s) to Base Unit

Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Range of Propeller Aircraft: 7126.017 Meter --> 7126.017 Meter No Conversion Required
Propeller Efficiency: 0.93 --> No Conversion Required
Gross Weight: 5000 Kilogram --> 5000 Kilogram No Conversion Required
Weight without Fuel: 3000 Kilogram --> 3000 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

LD = c*R_prop/(η*ln(W₀/W₁)) --> 0.000166666666666667*7126.017/(0.93*ln(5000/3000))

Evaluating ... ...

LD = 2.49999984158909

STEP 3: Convert Result to Output's Unit

2.49999984158909 --> No Conversion Required

FINAL ANSWER

2.49999984158909 ≈ 2.5 <-- Lift-to-Drag Ratio

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Range and Endurance » Aerospace » Propeller-Driven Airplane » Lift-to-Drag ratio for given Range of Propeller-Driven Airplane

Credits

Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has verified this Calculator and 200+ more calculators!

< 22 Propeller-Driven Airplane Calculators

Propeller Efficiency for given Endurance of Propeller-Driven Airplane

Go Propeller Efficiency = Endurance of Aircraft/((1/Specific Fuel Consumption)*((Lift Coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream Density*Reference Area))*(((1/Weight without Fuel)^(1/2))-((1/Gross Weight)^(1/2))))

Endurance of Propeller-Driven Airplane

Go Endurance of Propeller Aircraft = Propeller Efficiency/Specific Fuel Consumption*(Lift Coefficient^1.5)/Drag Coefficient*sqrt(2*Freestream Density*Reference Area)*((1/Weight without Fuel)^(1/2)-(1/Gross Weight)^(1/2))

Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane

Go Specific Fuel Consumption = Propeller Efficiency/Endurance of Aircraft*Lift Coefficient^1.5/Drag Coefficient*sqrt(2*Freestream Density*Reference Area)*((1/Weight without Fuel)^(1/2)-(1/Gross Weight)^(1/2))

Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft

Go Propeller Efficiency = (Preliminary Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Lift to Drag Ratio at Maximum Endurance*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))

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

Go 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))

Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft

Go Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance Prop*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance)

Specific Fuel Consumption for given Range of Propeller-Driven Airplane

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

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

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

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

Go 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))

Propeller Efficiency given Range for Prop-Driven Aircraft

Go Propeller Efficiency = (Range of Propeller Aircraft*Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))

Specific Fuel Consumption given Range for Prop-Driven Aircraft

Go Specific Fuel Consumption = (Propeller Efficiency*Maximum Lift-to-Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of Propeller Aircraft

Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane

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

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

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

Propeller Efficiency for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane

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

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

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

Cruise Weight Fraction for Prop-Driven Aircraft

Go Cruise Weight Fraction Propeller Aircraft = exp((Range of Propeller Aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio*Propeller Efficiency))

Propeller Efficiency for Reciprocating Engine-Propeller Combination

Go Propeller Efficiency = Available Power/Brake Power

Shaft Brake Power for Reciprocating Engine-Propeller Combination

Go Brake Power = Available Power/Propeller Efficiency

Power Available for Reciprocating Engine-Propeller Combination

Go Available Power = Propeller Efficiency*Brake Power

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

Go Lift to Drag Ratio at Maximum Endurance = 0.866*Maximum Lift-to-Drag Ratio

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

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

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

Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel))
LD = c*R_prop/(η*ln(W₀/W₁))

What does lift to drag ratio determine?

Lift/drag ratio determines the glide ratio and gliding range. Since the glide ratio is based only on the relationship of the aerodynamics forces acting on the aircraft, aircraft weight will not affect it. The only effect weight has is to vary the time that the aircraft will glide for.

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

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane calculator uses Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel)) to calculate 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 calculate Lift-to-Drag ratio for given Range of Propeller-Driven Airplane using this online calculator? To use this online calculator 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. Here is how the Lift-to-Drag ratio for given Range of Propeller-Driven Airplane calculation can be explained with given input values -> 2.499994 = 0.000166666666666667*7126.017/(0.93*ln(5000/3000)).

FAQ

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

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 and is represented as LD = c*R_prop/(η*ln(W₀/W₁)) or Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel)). Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), The Gross Weight of the airplane is the weight with full fuel and payload & Weight without Fuel is the total weight of the airplane without fuel.

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

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 is calculated using Lift-to-Drag Ratio = Specific Fuel Consumption*Range of Propeller Aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without Fuel)). To calculate Lift-to-Drag ratio for given Range of Propeller-Driven Airplane, you need Specific Fuel Consumption (c), Range of Propeller Aircraft (R_prop), Propeller Efficiency (η), Gross Weight (W₀) & Weight without Fuel (W₁). With our tool, you need to enter the respective value for Specific Fuel Consumption, Range of Propeller Aircraft, Propeller Efficiency, Gross Weight & Weight without Fuel 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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