Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft Calculator

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Propeller-Driven Airplane

✖Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flight.ⓘ Endurance of Aircraft [E]			+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%
✖Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase.ⓘ Weight at Start of Loiter Phase [W_L,beg]			+10% -10%
✖Weight at End of Loiter Phase is considered for the Preliminary Endurance Calculation. For the calculation of preliminary endurance, the loiter phase is considered.ⓘ Weight at End of Loiter Phase [W_L,end]			+10% -10%

✖Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.ⓘ Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft [LDmax_ratio]

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Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft

Formula

`"LDmax"_{"ratio"} = ("E"*"c")/ln("W"_{"L,beg"}/"W"_{"L,end"})`

Example

`"5.079376"=("452.873s"*"0.6kg/h/W")/ln("400kg"/"394.1kg")`

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Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Maximum Lift to Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)
LDmax_ratio = (E*c)/ln(W_L,beg/W_L,end)
This formula uses 1 Functions, 5 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 - Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.
Endurance of Aircraft - (Measured in Second) - Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flight.
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.
Weight at Start of Loiter Phase - (Measured in Kilogram) - Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase.
Weight at End of Loiter Phase - (Measured in Kilogram) - Weight at End of Loiter Phase is considered for the Preliminary Endurance Calculation. For the calculation of preliminary endurance, the loiter phase is considered.

STEP 1: Convert Input(s) to Base Unit

Endurance of Aircraft: 452.873 Second --> 452.873 Second No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Weight at Start of Loiter Phase: 400 Kilogram --> 400 Kilogram No Conversion Required
Weight at End of Loiter Phase: 394.1 Kilogram --> 394.1 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

LDmax_ratio = (E*c)/ln(W_L,beg/W_L,end) --> (452.873*0.000166666666666667)/ln(400/394.1)

Evaluating ... ...

LDmax_ratio = 5.07937615613235

STEP 3: Convert Result to Output's Unit

5.07937615613235 --> No Conversion Required

FINAL ANSWER

5.07937615613235 ≈ 5.079376 <-- Maximum Lift to Drag Ratio

(Calculation completed in 00.004 seconds)

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< 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))

Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft Formula

Maximum Lift to Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)
LDmax_ratio = (E*c)/ln(W_L,beg/W_L,end)

What do you mean by Endurance of Aircraft?

In aviation, endurance is the maximum length of time that an aircraft can spend in cruising flight. In other words, it is the amount of time an aircraft can stay in the air with one load of fuel. Endurance is different from range, which is a measure of distance flown. For example, a typical sailplane exhibits high endurance characteristics but poor range characteristics. Endurance can factor into aviation design in a number of ways. Some aircraft, require high endurance characteristics as part of their mission profile (often referred to as loiter time). Endurance plays a prime factor in finding out the fuel fraction for an aircraft. Endurance, like range, is also related to fuel efficiency; fuel-efficient aircraft will tend to exhibit good endurance characteristics.

How to Calculate Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft?

Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft calculator uses Maximum Lift to Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase) to calculate the Maximum Lift to Drag Ratio, The Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft formula is defined as the maximum value of the lift to drag ratio for the calculation of Maximum Endurance of Jet Aircraft. Maximum Lift to Drag Ratio is denoted by LDmax_ratio symbol.

How to calculate Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft using this online calculator? To use this online calculator for Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft, enter Endurance of Aircraft (E), Specific Fuel Consumption (c), Weight at Start of Loiter Phase (W_L,beg) & Weight at End of Loiter Phase (W_L,end) and hit the calculate button. Here is how the Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft calculation can be explained with given input values -> 0.262369 = (452.873*0.000166666666666667)/ln(400/394.1).

FAQ

What is Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft?

The Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft formula is defined as the maximum value of the lift to drag ratio for the calculation of Maximum Endurance of Jet Aircraft and is represented as LDmax_ratio = (E*c)/ln(W_L,beg/W_L,end) or Maximum Lift to Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase). Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flight, Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase & Weight at End of Loiter Phase is considered for the Preliminary Endurance Calculation. For the calculation of preliminary endurance, the loiter phase is considered.

How to calculate Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft?

The Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft formula is defined as the maximum value of the lift to drag ratio for the calculation of Maximum Endurance of Jet Aircraft is calculated using Maximum Lift to Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase). To calculate Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft, you need Endurance of Aircraft (E), Specific Fuel Consumption (c), Weight at Start of Loiter Phase (W_L,beg) & Weight at End of Loiter Phase (W_L,end). With our tool, you need to enter the respective value for Endurance of Aircraft, Specific Fuel Consumption, Weight at Start of Loiter Phase & Weight at End of Loiter 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 Endurance of Aircraft, Specific Fuel Consumption, Weight at Start of Loiter Phase & Weight at End of Loiter Phase. We can use 1 other way(s) to calculate the same, which is/are as follows -

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))

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