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Maximum Lift over Drag Formula

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Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight. Check FAQs

LDmax ratio = K LD \cdot {(\frac{AR}{\frac{S wet}{S}})}^{0.5}

LDmax_ratio - Maximum Lift-to-Drag Ratio of Aircraft?K_LD - Landing Mass Fraction?AR - Aspect Ratio of a Wing?S_wet - Aircraft Wetted Area?S - Reference Area?

Maximum Lift over Drag Example

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Here is how the Maximum Lift over Drag equation looks like with Values.

Here is how the Maximum Lift over Drag equation looks like with Units.

Here is how the Maximum Lift over Drag equation looks like.

19.799 = 14 \cdot {(\frac{4}{\frac{10.16}{5.08}})}^{0.5}

19.799 = 14 \cdot {(\frac{4}{\frac{10.16m²}{5.08m²}})}^{0.5}

19.799 = 14 \cdot {(\frac{4}{\frac{10.16}{5.08}})}^{0.5}

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Maximum Lift over Drag Solution

Follow our step by step solution on how to calculate Maximum Lift over Drag?

FIRST Step Consider the formula

LDmax ratio = K LD \cdot {(\frac{AR}{\frac{S wet}{S}})}^{0.5}

Next Step Substitute values of Variables

∴

LDmax ratio = 14 \cdot {(\frac{4}{\frac{10.16m²}{5.08m²}})}^{0.5}

Next Step Prepare to Evaluate

∴

LDmax ratio = 14 \cdot {(\frac{4}{\frac{10.16}{5.08}})}^{0.5}

Next Step Evaluate

∴

LDmax ratio = 19.7989898732233

LAST Step Rounding Answer

∴

LDmax ratio = 19.799

Maximum Lift over Drag Formula Elements

Variables

Maximum Lift-to-Drag Ratio of Aircraft

Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.

Symbol: LDmax_ratio

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Maximum Lift-to-Drag Ratio of Aircraft

Landing Mass Fraction

Landing Mass Fraction is a constant that depends on the various different aircraft types.

Symbol: K_LD

Measurement: NAUnit: Unitless

Note: Value should be between 8 to 16.

Formulas to find Landing Mass Fraction

Aspect Ratio of a Wing

The Aspect Ratio of a Wing is defined as the ratio of its span to its mean chord.

Symbol: AR

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Aspect Ratio of a Wing

Aircraft Wetted Area

The Aircraft Wetted Area is the surface area that interacts with the working fluid or gas.

Symbol: S_wet

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Aircraft Wetted Area

Reference Area

The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.

Symbol: S

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Reference Area

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How to Evaluate Maximum Lift over Drag?

Maximum Lift over Drag evaluator uses Maximum Lift-to-Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5) to evaluate the Maximum Lift-to-Drag Ratio of Aircraft, The Maximum Lift over Drag formula represents the efficiency of an aircraft or airfoil in generating lift compared to the drag it produces, this formula calculates the maximum lift-to-drag ratio by considering the landing mass fraction, aspect ratio of the wing, and the ratio of the wetted area of the aircraft to the reference area, with appropriate scaling factors. Maximum Lift-to-Drag Ratio of Aircraft is denoted by LDmax_ratio symbol.

How to evaluate Maximum Lift over Drag using this online evaluator? To use this online evaluator for Maximum Lift over Drag, enter Landing Mass Fraction (K_LD), Aspect Ratio of a Wing (AR), Aircraft Wetted Area (S_wet) & Reference Area (S) and hit the calculate button.

FAQs on Maximum Lift over Drag

What is the formula to find Maximum Lift over Drag?

The formula of Maximum Lift over Drag is expressed as Maximum Lift-to-Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5). Here is an example- 19.79899 = 14*((4)/(10.16/5.08))^(0.5).

How to calculate Maximum Lift over Drag?

With Landing Mass Fraction (K_LD), Aspect Ratio of a Wing (AR), Aircraft Wetted Area (S_wet) & Reference Area (S) we can find Maximum Lift over Drag using the formula - Maximum Lift-to-Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5).

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Maximum Lift over Drag Formula

Maximum Lift over Drag Example

Maximum Lift over Drag Solution

Maximum Lift over Drag Formula Elements

Other formulas in Preliminary Design category

How to Evaluate Maximum Lift over Drag?

FAQs on Maximum Lift over Drag

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