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

✖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%
✖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%
✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+10% -10%
✖Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.ⓘ Weight at Start of Cruise Phase [W_i]			+10% -10%
✖Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.ⓘ Weight at End of Cruise Phase [W_f]			+10% -10%

✖The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.ⓘ Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft [LDmax_ratio]

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

STEP 0: Pre-Calculation Summary

Formula Used

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))
LDmax_ratio = (R_prop*c)/(η*ln(W_i/W_f))
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

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.
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.
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.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
Weight at Start of Cruise Phase - (Measured in Kilogram) - Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.
Weight at End of Cruise Phase - (Measured in Kilogram) - Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

STEP 1: Convert Input(s) to Base Unit

Range of Propeller Aircraft: 7126.017 Meter --> 7126.017 Meter No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Propeller Efficiency: 0.93 --> No Conversion Required
Weight at Start of Cruise Phase: 450 Kilogram --> 450 Kilogram No Conversion Required
Weight at End of Cruise Phase: 350 Kilogram --> 350 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

LDmax_ratio = (R_prop*c)/(η*ln(W_i/W_f)) --> (7126.017*0.000166666666666667)/(0.93*ln(450/350))

Evaluating ... ...

LDmax_ratio = 5.08153864157449

STEP 3: Convert Result to Output's Unit

5.08153864157449 --> No Conversion Required

FINAL ANSWER

5.08153864157449 ≈ 5.081539 <-- Maximum Lift-to-Drag Ratio

(Calculation completed in 00.004 seconds)

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Created by Vedant Chitte

All India Shri Shivaji Memorials Society's ,College of Engineering (AISSMS COE PUNE), Pune

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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))

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

LaTeX Go

What is Lift to Drag ratio of an aircraft?

In aerodynamics, the lift-to-drag ratio (or L/D ratio) is the lift generated by an aerodynamic body such as an airfoil or aircraft, divided by the aerodynamic drag caused by moving through air. It describes the aerodynamic efficiency under given flight conditions. The L/D ratio for any given body will vary according to these flight conditions. For an airfoil wing or powered aircraft, the L/D is specified when in straight and level flight. For a glider, it determines the glide ratio, of distance traveled against loss of height. The term is calculated for any particular airspeed by measuring the lift generated, then dividing by the drag at that speed. These vary with speed, so the results are typically plotted on a 2-dimensional graph. The L/D may be calculated using computational fluid dynamics or computer simulation. It is measured empirically by testing in a wind tunnel or free-flight test.

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

Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft calculator 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 calculate 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 calculate Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft using this online calculator? To use this online calculator 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. Here is how the Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft calculation can be explained with given input values -> 5.081539 = (7126.017*0.000166666666666667)/(0.93*ln(450/350)).

FAQ

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

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 and is represented as LDmax_ratio = (R_prop*c)/(η*ln(W_i/W_f)) or 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)). Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission & Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

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

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 is calculated using 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 calculate Maximum Lift to Drag Ratio given Range for Prop-Driven Aircraft, you need 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). With our tool, you need to enter the respective value for Range of Propeller Aircraft, Specific Fuel Consumption, Propeller Efficiency, Weight at Start of Cruise Phase & Weight at End of Cruise Phase 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 Maximum Lift-to-Drag Ratio?

In this formula, Maximum Lift-to-Drag Ratio uses Range of Propeller Aircraft, Specific Fuel Consumption, Propeller Efficiency, Weight at Start of Cruise Phase & Weight at End of Cruise Phase. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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