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Maximum Lift to Drag Ratio given Range for Jet Aircraft Formula

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Maximum Lift to Drag Ratio Jet Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value. Check FAQs

LDmax ratio prop = \frac{R jet \cdot c}{V L/D,max \cdot \ln (\frac{W i}{W f})}

LDmax_{ratio prop} - Maximum Lift to Drag Ratio Jet Aircraft?R_jet - Range of Jet Aircraft?c - Specific Fuel Consumption?V_L/D,max - Velocity at Maximum Lift to Drag Ratio?W_i - Weight at Start of Cruise Phase?W_f - Weight at End of Cruise Phase?

Maximum Lift to Drag Ratio given Range for Jet Aircraft Example

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Here is how the Maximum Lift to Drag Ratio given Range for Jet Aircraft equation looks like with Values.

Here is how the Maximum Lift to Drag Ratio given Range for Jet Aircraft equation looks like with Units.

Here is how the Maximum Lift to Drag Ratio given Range for Jet Aircraft equation looks like.

4.5033 = \frac{7130 \cdot 0.6}{1.05 \cdot \ln (\frac{450}{350})}

4.5033 = \frac{7130m \cdot 0.6kg/h/W}{1.05m/s \cdot \ln (\frac{450kg}{350kg})}

4.5033 = \frac{7130 \cdot 0.6}{1.05 \cdot \ln (\frac{450}{350})}

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Maximum Lift to Drag Ratio given Range for Jet Aircraft Solution

Follow our step by step solution on how to calculate Maximum Lift to Drag Ratio given Range for Jet Aircraft?

FIRST Step Consider the formula

LDmax ratio prop = \frac{R jet \cdot c}{V L/D,max \cdot \ln (\frac{W i}{W f})}

Next Step Substitute values of Variables

∴

LDmax ratio prop = \frac{7130m \cdot 0.6kg/h/W}{1.05m/s \cdot \ln (\frac{450kg}{350kg})}

Next Step Convert Units

∴

LDmax ratio prop = \frac{7130m \cdot 0.0002kg/s/W}{1.05m/s \cdot \ln (\frac{450kg}{350kg})}

Next Step Prepare to Evaluate

∴

LDmax ratio prop = \frac{7130 \cdot 0.0002}{1.05 \cdot \ln (\frac{450}{350})}

Next Step Evaluate

∴

LDmax ratio prop = 4.50330703051011

LAST Step Rounding Answer

∴

LDmax ratio prop = 4.5033

Maximum Lift to Drag Ratio given Range for Jet Aircraft Formula Elements

Variables

Functions

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.

Symbol: LDmax_{ratio prop}

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Maximum Lift to Drag Ratio Jet Aircraft

Range of Jet Aircraft

Range of Jet Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.

Symbol: R_jet

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Range of Jet Aircraft

Specific Fuel Consumption

Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.

Symbol: c

Measurement: Specific Fuel ConsumptionUnit: kg/h/W

Note: Value should be greater than 0.

Formulas to find Specific Fuel Consumption

Velocity at Maximum Lift to Drag Ratio

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.

Symbol: V_L/D,max

Measurement: SpeedUnit: m/s

Note: Value should be greater than 0.

Formulas to find Velocity at Maximum Lift to Drag Ratio

Weight at Start of Cruise Phase

Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.

Symbol: W_i

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight at Start of Cruise Phase

Weight at End of Cruise Phase

Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

Symbol: W_f

Measurement: WeightUnit: kg

Note: Value should be greater than 0.

Formulas to find Weight at End of Cruise Phase

The natural logarithm, also known as the logarithm to the base e, is the inverse function of the natural exponential function.

Syntax: ln(Number)

Other formulas in Jet Airplane category

Go Endurance of Jet Airplane

E = C L \cdot \frac{\ln (\frac{W 0}{W 1})}{C D \cdot c t}

Go Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

c t = C L \cdot \frac{\ln (\frac{W 0}{W 1})}{C D \cdot E}

Go Endurance for given Lift-to-Drag Ratio of Jet Airplane

E = (\frac{1}{c t}) \cdot LD \cdot \ln (\frac{W 0}{W 1})

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

c t = (\frac{1}{E}) \cdot LD \cdot \ln (\frac{W 0}{W 1})

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

Maximum Lift to Drag Ratio given Range for Jet Aircraft evaluator 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 evaluate 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 evaluate Maximum Lift to Drag Ratio given Range for Jet Aircraft using this online evaluator? To use this online evaluator 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.

FAQs on Maximum Lift to Drag Ratio given Range for Jet Aircraft

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

The formula of Maximum Lift to Drag Ratio given Range for Jet Aircraft is expressed as 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)). Here is an example- 4.503307 = (7130*0.000166666666666667)/(1.05*ln(450/350)).

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

With 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) we can find Maximum Lift to Drag Ratio given Range for Jet Aircraft using the formula - 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)). This formula also uses Natural Logarithm (ln) function(s).

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Maximum Lift to Drag Ratio given Range for Jet Aircraft Formula

Maximum Lift to Drag Ratio given Range for Jet Aircraft Example

Maximum Lift to Drag Ratio given Range for Jet Aircraft Solution

Maximum Lift to Drag Ratio given Range for Jet Aircraft Formula Elements

Other formulas in Jet Airplane category

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

FAQs on Maximum Lift to Drag Ratio given Range for Jet Aircraft

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