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

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Aircraft Performance

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Propeller-Driven Airplane

✖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 aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Range of aircraft [R]			+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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Formula

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

Formula

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

Example

`"2.499994"="0.6kg/h/W"*"7126m"/("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 aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without fuel))
LD = c*R/(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 aircraft - (Measured in Meter) - Range of 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 aircraft: 7126 Meter --> 7126 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/(η*ln(W₀/W₁)) --> 0.000166666666666667*7126/(0.93*ln(5000/3000))

Evaluating ... ...

LD = 2.49999387752848

STEP 3: Convert Result to Output's Unit

2.49999387752848 --> No Conversion Required

FINAL ANSWER

2.49999387752848 ≈ 2.499994 <-- Lift-to-drag ratio

(Calculation completed in 00.004 seconds)

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

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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!

< 18 Jet Airplane Calculators

Thrust-Specific Fuel Consumption for given Range of Jet Airplane

Go Thrust-Specific Fuel Consumption = (sqrt(8/(Freestream density*Reference Area)))*(1/(Range of aircraft*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel)))

Range of Jet Airplane

Go Range of aircraft = (sqrt(8/(Freestream density*Reference Area)))*(1/(Thrust-Specific Fuel Consumption*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel)))

Maximum Lift to Drag Ratio given Range for Jet Aircraft

Go Maximum Lift to Drag Ratio = (Range of aircraft*Specific Fuel Consumption)/(Velocity at Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))

Specific Fuel Consumption given Range for Jet Aircraft

Go Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft

Breguet Range

Go Range of aircraft = (Lift-to-drag ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)

Breguet Endurance Equation

Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*(Lift Coefficient/Drag Coefficient)*ln(Gross Weight/Weight without fuel)

Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

Go Thrust-Specific Fuel Consumption = Lift Coefficient*(ln(Gross Weight/Weight without fuel))/(Drag Coefficient*Endurance of Aircraft)

Endurance of Jet Airplane

Go Endurance of Aircraft = Lift Coefficient*(ln(Gross Weight/Weight without fuel))/(Drag Coefficient*Thrust-Specific Fuel Consumption)

Cruise Weight Fraction for Jet Aircraft

Go Cruise Weight Fraction = exp((Range of aircraft*Specific Fuel Consumption*(-1))/(0.866*1.32*Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio))

Constant Speed Cruise using Range Equation

Go Range of aircraft = Flight Velocity/(Thrust-Specific Fuel Consumption*Total Thrust)*int(1,x,Weight without fuel,Gross Weight)

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

Go Lift-to-drag ratio = Specific Fuel Consumption*Range of aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without fuel))

Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft

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

Specific Fuel Consumption given Preliminary Endurance for Jet Aircraft

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

Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane

Go Thrust-Specific Fuel Consumption = (1/Endurance of Aircraft)*Lift-to-drag ratio*ln(Gross Weight/Weight without fuel)

Endurance for given Lift-to-Drag ratio of Jet Airplane

Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*Lift-to-drag ratio*ln(Gross Weight/Weight without fuel)

Lift-to-Drag ratio for given Endurance of Jet Airplane

Go Lift-to-drag ratio = Thrust-Specific Fuel Consumption*Endurance of Aircraft/(ln(Gross Weight/Weight without fuel))

Loiter Weight Fraction for Jet Aircraft

Go Loiter weight Fraction for Jet aircraft = exp(((-1)*Endurance of Aircraft*Specific Fuel Consumption)/Maximum Lift to Drag Ratio)

Average Value Range Equation

Go Average Value Range Equation = Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity))

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

Lift-to-drag ratio = Specific Fuel Consumption*Range of aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without fuel))
LD = c*R/(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 aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without fuel)) to calculate the Lift-to-drag ratio, The Lift-to-Drag ratio for given Range of Propeller-Driven Airplane is a function of specific fuel consumption, propeller efficiency, gross weight, and the weight without the fuel of aircraft. 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 aircraft (R), 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/(0.93*ln(5000/3000)).

FAQ

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

The Lift-to-Drag ratio for given Range of Propeller-Driven Airplane is a function of specific fuel consumption, propeller efficiency, gross weight, and the weight without the fuel of aircraft and is represented as LD = c*R/(η*ln(W₀/W₁)) or Lift-to-drag ratio = Specific Fuel Consumption*Range of 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 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?

The Lift-to-Drag ratio for given Range of Propeller-Driven Airplane is a function of specific fuel consumption, propeller efficiency, gross weight, and the weight without the fuel of aircraft is calculated using Lift-to-drag ratio = Specific Fuel Consumption*Range of 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 aircraft (R), 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 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.

How many ways are there to calculate Lift-to-drag ratio?

In this formula, Lift-to-drag ratio uses Specific Fuel Consumption, Range of aircraft, Propeller Efficiency, Gross Weight & Weight without fuel. We can use 1 other way(s) to calculate the same, which is/are as follows -

Lift-to-drag ratio = Thrust-Specific Fuel Consumption*Endurance of Aircraft/(ln(Gross Weight/Weight without fuel))

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