Maximum Lift to Drag Ratio given Range for Jet Aircraft Calculator

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Propeller-Driven Airplane

✖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%
✖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%
✖Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.ⓘ Velocity at Maximum Lift to Drag Ratio [V_L/D,max]			+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%

✖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 Range for Jet Aircraft [LDmax_ratio]

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Formula

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Maximum Lift to Drag Ratio given Range for Jet Aircraft

Formula

`"LDmax"_{"ratio"} = ("R"*"c")/("V"_{"L/D,max"}*ln("W"_{"i"}/"W"_{"f"}))`

Example

`"0.094516"=("7126m"*"0.6kg/h/W")/("50m/s"*ln("450kg"/"350kg"))`

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Maximum Lift to Drag Ratio given Range for Jet Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

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))
LDmax_ratio = (R*c)/(V_L/D,max*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 - Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.
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.
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.
Velocity at Maximum Lift to Drag Ratio - (Measured in Meter per Second) - Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.
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 aircraft: 7126 Meter --> 7126 Meter No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Velocity at Maximum Lift to Drag Ratio: 50 Meter per Second --> 50 Meter per Second 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*c)/(V_L/D,max*ln(W_i/W_f)) --> (7126*0.000166666666666667)/(50*ln(450/350))

Evaluating ... ...

LDmax_ratio = 0.0945163932521341

STEP 3: Convert Result to Output's Unit

0.0945163932521341 --> No Conversion Required

FINAL ANSWER

0.0945163932521341 ≈ 0.094516 <-- Maximum Lift to Drag Ratio

(Calculation completed in 00.006 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Range and Endurance » Jet Airplane » Maximum Lift to Drag Ratio given Range for Jet Aircraft

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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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< 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 Range for Jet Aircraft Formula

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 in free flight test.

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

Maximum Lift to Drag Ratio given Range for Jet Aircraft calculator uses 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)) to calculate the Maximum Lift to Drag Ratio, The Maximum Lift to Drag Ratio given Range for Jet Aircraft formula is defined as the ratio of the coefficient of lift to the coefficient of drag and considered to be maximum in the magnitude so the range is maximum. Maximum Lift to Drag Ratio is denoted by LDmax_ratio symbol.

How to calculate Maximum Lift to Drag Ratio given Range for Jet Aircraft using this online calculator? To use this online calculator for Maximum Lift to Drag Ratio given Range for Jet Aircraft, enter Range of aircraft (R), Specific Fuel Consumption (c), Velocity at Maximum Lift to Drag Ratio (V_L/D,max), 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 Jet Aircraft calculation can be explained with given input values -> 1.202743 = (7126*0.000166666666666667)/(50*ln(450/350)).

FAQ

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

The Maximum Lift to Drag Ratio given Range for Jet Aircraft formula is defined as the ratio of the coefficient of lift to the coefficient of drag and considered to be maximum in the magnitude so the range is maximum and is represented as LDmax_ratio = (R*c)/(V_L/D,max*ln(W_i/W_f)) or 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)). Range of 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, Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase, 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 Jet Aircraft?

The Maximum Lift to Drag Ratio given Range for Jet Aircraft formula is defined as the ratio of the coefficient of lift to the coefficient of drag and considered to be maximum in the magnitude so the range is maximum is calculated using 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)). To calculate Maximum Lift to Drag Ratio given Range for Jet Aircraft, you need Range of aircraft (R), Specific Fuel Consumption (c), Velocity at Maximum Lift to Drag Ratio (V_L/D,max), 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 aircraft, Specific Fuel Consumption, Velocity at Maximum Lift to Drag Ratio, 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 aircraft, Specific Fuel Consumption, Velocity at Maximum Lift to Drag Ratio, 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 = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)

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