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

✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+10% -10%
✖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%
✖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 [LD]			+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%

✖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-Driven Airplane for given lift-to-drag ratio [R_prop]

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

STEP 0: Pre-Calculation Summary

Formula Used

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

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).
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.
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.
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

Propeller Efficiency: 0.93 --> No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Lift-to-Drag Ratio: 2.5 --> 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

R_prop = (η/c)*(LD)*(ln(W₀/W₁)) --> (0.93/0.000166666666666667)*(2.5)*(ln(5000/3000))

Evaluating ... ...

R_prop = 7126.01745153556

STEP 3: Convert Result to Output's Unit

7126.01745153556 Meter --> No Conversion Required

FINAL ANSWER

7126.01745153556 ≈ 7126.017 Meter <-- Range of Propeller Aircraft

(Calculation completed in 00.004 seconds)

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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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< Propeller Driven Airplane Calculators

Specific Fuel Consumption for given Range of Propeller-Driven Airplane

LaTeX 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

LaTeX 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

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

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

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

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

LaTeX Go

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

How is the range affected by the lift-to-drag ratio?

An aircraft with a high Lift-to-Drag ratio can carry a large payload, for a long time, over a long distance.

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

Range of Propeller-Driven Airplane for given lift-to-drag ratio calculator uses Range of Propeller Aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel)) to calculate the Range of Propeller Aircraft, Range of Propeller-Driven Airplane for given lift-to-drag ratio is a measure of the maximum distance an airplane can travel, taking into account the efficiency of the propeller, the lift-to-drag ratio, and the weight of the aircraft. It calculates the range of an airplane for a given lift-to-drag ratio, providing valuable insights into the aircraft's performance and capabilities. This formula is essential in aerodynamics and aircraft design. Range of Propeller Aircraft is denoted by R_prop symbol.

How to calculate Range of Propeller-Driven Airplane for given lift-to-drag ratio using this online calculator? To use this online calculator for Range of Propeller-Driven Airplane for given lift-to-drag ratio, enter Propeller Efficiency (η), Specific Fuel Consumption (c), Lift-to-Drag Ratio (LD), Gross Weight (W₀) & Weight without Fuel (W₁) and hit the calculate button. Here is how the Range of Propeller-Driven Airplane for given lift-to-drag ratio calculation can be explained with given input values -> 7126.017 = (0.93/0.000166666666666667)*(2.5)*(ln(5000/3000)).

FAQ

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

Range of Propeller-Driven Airplane for given lift-to-drag ratio is a measure of the maximum distance an airplane can travel, taking into account the efficiency of the propeller, the lift-to-drag ratio, and the weight of the aircraft. It calculates the range of an airplane for a given lift-to-drag ratio, providing valuable insights into the aircraft's performance and capabilities. This formula is essential in aerodynamics and aircraft design and is represented as R_prop = (η/c)*(LD)*(ln(W₀/W₁)) or Range of Propeller Aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel)). Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, 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, 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 Range of Propeller-Driven Airplane for given lift-to-drag ratio?

Range of Propeller-Driven Airplane for given lift-to-drag ratio is a measure of the maximum distance an airplane can travel, taking into account the efficiency of the propeller, the lift-to-drag ratio, and the weight of the aircraft. It calculates the range of an airplane for a given lift-to-drag ratio, providing valuable insights into the aircraft's performance and capabilities. This formula is essential in aerodynamics and aircraft design is calculated using Range of Propeller Aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel)). To calculate Range of Propeller-Driven Airplane for given lift-to-drag ratio, you need Propeller Efficiency (η), Specific Fuel Consumption (c), Lift-to-Drag Ratio (LD), Gross Weight (W₀) & Weight without Fuel (W₁). With our tool, you need to enter the respective value for Propeller Efficiency, Specific Fuel Consumption, Lift-to-Drag Ratio, 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 Range of Propeller Aircraft?

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

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

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