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Total Lift Coefficient of Wing-Tail Combination Formula

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The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. Check FAQs

C L = CW lift + (η \cdot S t \cdot \frac{CT lift}{S})

C_L - Lift Coefficient?CW_lift - Wing Lift Coefficient?η - Tail Efficiency?S_t - Horizontal Tail Area?CT_lift - Tail Lift Coefficient?S - Reference Area?

Total Lift Coefficient of Wing-Tail Combination Example

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Here is how the Total Lift Coefficient of Wing-Tail Combination equation looks like with Values.

Here is how the Total Lift Coefficient of Wing-Tail Combination equation looks like with Units.

Here is how the Total Lift Coefficient of Wing-Tail Combination equation looks like.

1.1078 = 1.01 + (0.92 \cdot 1.8 \cdot \frac{0.3}{5.08})

1.1078 = 1.01 + (0.92 \cdot 1.8m² \cdot \frac{0.3}{5.08m²})

1.1078 = 1.01 + (0.92 \cdot 1.8 \cdot \frac{0.3}{5.08})

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Total Lift Coefficient of Wing-Tail Combination Solution

Follow our step by step solution on how to calculate Total Lift Coefficient of Wing-Tail Combination?

FIRST Step Consider the formula

C L = CW lift + (η \cdot S t \cdot \frac{CT lift}{S})

Next Step Substitute values of Variables

∴

C L = 1.01 + (0.92 \cdot 1.8m² \cdot \frac{0.3}{5.08m²})

Next Step Prepare to Evaluate

∴

C L = 1.01 + (0.92 \cdot 1.8 \cdot \frac{0.3}{5.08})

Next Step Evaluate

∴

C L = 1.10779527559055

LAST Step Rounding Answer

∴

C L = 1.1078

Total Lift Coefficient of Wing-Tail Combination Formula Elements

Variables

Lift Coefficient

The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.

Symbol: C_L

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient

Wing Lift Coefficient

Wing Lift Coefficient is the lift coefficient associated with the wing (only) of an aircraft. It is a dimensionless quantity.

Symbol: CW_lift

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Wing Lift Coefficient

Tail Efficiency

Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.

Symbol: η

Measurement: NAUnit: Unitless

Note: Value should be between 0.8 to 1.2.

Formulas to find Tail Efficiency

Horizontal Tail Area

The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.

Symbol: S_t

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Horizontal Tail Area

Tail Lift Coefficient

Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.

Symbol: CT_lift

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Tail Lift Coefficient

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

Other formulas in Wing Tail Contribution category

Go Angle of Attack at Tail

α t = α w - 𝒊 w - ε + 𝒊 t

Go Angle of Attack of Wing

α w = α t + 𝒊 w + ε - 𝒊 t

Go Angle of incidence of wing

𝒊 w = α w - α t - ε + 𝒊 t

Go Downwash angle

ε = α w - 𝒊 w - α t + 𝒊 t

How to Evaluate Total Lift Coefficient of Wing-Tail Combination?

Total Lift Coefficient of Wing-Tail Combination evaluator uses Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal Tail Area*Tail Lift Coefficient/Reference Area) to evaluate the Lift Coefficient, Total Lift Coefficient of Wing-Tail Combination is a measure of the overall lifting ability of an aircraft, taking into account the individual lift coefficients of the wing and tail, as well as the efficiency of the tail and its area relative to the reference area. Lift Coefficient is denoted by C_L symbol.

How to evaluate Total Lift Coefficient of Wing-Tail Combination using this online evaluator? To use this online evaluator for Total Lift Coefficient of Wing-Tail Combination, enter Wing Lift Coefficient (CW_lift), Tail Efficiency (η), Horizontal Tail Area (S_t), Tail Lift Coefficient (CT_lift) & Reference Area (S) and hit the calculate button.

FAQs on Total Lift Coefficient of Wing-Tail Combination

What is the formula to find Total Lift Coefficient of Wing-Tail Combination?

The formula of Total Lift Coefficient of Wing-Tail Combination is expressed as Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal Tail Area*Tail Lift Coefficient/Reference Area). Here is an example- 1.107795 = 1.01+(0.92*1.8*0.3/5.08).

How to calculate Total Lift Coefficient of Wing-Tail Combination?

With Wing Lift Coefficient (CW_lift), Tail Efficiency (η), Horizontal Tail Area (S_t), Tail Lift Coefficient (CT_lift) & Reference Area (S) we can find Total Lift Coefficient of Wing-Tail Combination using the formula - Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal Tail Area*Tail Lift Coefficient/Reference Area).

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Total Lift Coefficient of Wing-Tail Combination Formula

Total Lift Coefficient of Wing-Tail Combination Example

Total Lift Coefficient of Wing-Tail Combination Solution

Total Lift Coefficient of Wing-Tail Combination Formula Elements

Other formulas in Wing Tail Contribution category

How to Evaluate Total Lift Coefficient of Wing-Tail Combination?

FAQs on Total Lift Coefficient of Wing-Tail Combination

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