Maximum Lift to Drag Ratio given Range for Jet Aircraft Calculator

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

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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 Jet Aircraft = (Range of Jet 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 prop} = (R_jet*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 Jet Aircraft - Maximum Lift to Drag Ratio Jet Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.
Range of Jet Aircraft - (Measured in Meter) - Range of Jet 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 Jet Aircraft: 7130 Meter --> 7130 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: 1.05 Meter per Second --> 1.05 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 prop} = (R_jet*c)/(V_L/D,max*ln(W_i/W_f)) --> (7130*0.000166666666666667)/(1.05*ln(450/350))

Evaluating ... ...

LDmax_{ratio prop} = 4.50330703051011

STEP 3: Convert Result to Output's Unit

4.50330703051011 --> No Conversion Required

FINAL ANSWER

4.50330703051011 ≈ 4.503307 <-- Maximum Lift to Drag Ratio Jet Aircraft

(Calculation completed in 00.004 seconds)

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< Jet Airplane Calculators

Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

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

Endurance of Jet Airplane

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

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

LaTeX 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

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

Maximum Lift to Drag Ratio given Range for Jet 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 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 Jet Aircraft = (Range of Jet 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 Jet Aircraft, Maximum Lift to Drag Ratio given Range for Jet Aircraft is a measure of the optimal aerodynamic performance of a jet aircraft, considering its range, specific fuel consumption, and weight during cruise, it represents the highest lift-to-drag ratio achievable by the aircraft at a given range, allowing for efficient fuel consumption and optimized flight performance. Maximum Lift to Drag Ratio Jet Aircraft is denoted by LDmax_{ratio prop} 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 Jet Aircraft (R_jet), 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 -> 4.503307 = (7130*0.000166666666666667)/(1.05*ln(450/350)).

FAQ

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

Maximum Lift to Drag Ratio given Range for Jet Aircraft is a measure of the optimal aerodynamic performance of a jet aircraft, considering its range, specific fuel consumption, and weight during cruise, it represents the highest lift-to-drag ratio achievable by the aircraft at a given range, allowing for efficient fuel consumption and optimized flight performance and is represented as LDmax_{ratio prop} = (R_jet*c)/(V_L/D,max*ln(W_i/W_f)) or Maximum Lift to Drag Ratio Jet Aircraft = (Range of Jet 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 Jet 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?

Maximum Lift to Drag Ratio given Range for Jet Aircraft is a measure of the optimal aerodynamic performance of a jet aircraft, considering its range, specific fuel consumption, and weight during cruise, it represents the highest lift-to-drag ratio achievable by the aircraft at a given range, allowing for efficient fuel consumption and optimized flight performance is calculated using Maximum Lift to Drag Ratio Jet Aircraft = (Range of Jet 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 Jet Aircraft (R_jet), 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 Jet 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.

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