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Vertical Tail Lift Curve Slope Formula

GoVertical Tail Lift Curve Slope for Given Moment Formula

GoVertical Tail Lift Curve Slope for given Vertical Tail Efficiency Formula

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The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft. Check FAQs

C v = - (\frac{Y v}{α v \cdot Q v \cdot S v})

C_v - Vertical Tail Lift Curve Slope?Y_v - Vertical Tail Side Force?α_v - Vertical Tail Angle of Attack?Q_v - Vertical Tail Dynamic Pressure?S_v - Vertical Tail Area?

Vertical Tail Lift Curve Slope Example

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Here is how the Vertical Tail Lift Curve Slope equation looks like with Values.

Here is how the Vertical Tail Lift Curve Slope equation looks like with Units.

Here is how the Vertical Tail Lift Curve Slope equation looks like.

0.6581 = - (\frac{-4.235}{0.117 \cdot 11 \cdot 5})

0.6581rad⁻¹ = - (\frac{-4.235N}{0.117rad \cdot 11Pa \cdot 5m²})

0.6581 = - (\frac{-4.235}{0.117 \cdot 11 \cdot 5})

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Vertical Tail Lift Curve Slope Solution

Follow our step by step solution on how to calculate Vertical Tail Lift Curve Slope?

FIRST Step Consider the formula

C v = - (\frac{Y v}{α v \cdot Q v \cdot S v})

Next Step Substitute values of Variables

∴

C v = - (\frac{-4.235N}{0.117rad \cdot 11Pa \cdot 5m²})

Next Step Prepare to Evaluate

∴

C v = - (\frac{-4.235}{0.117 \cdot 11 \cdot 5})

Next Step Evaluate

∴

C v = 0.658119658119658rad⁻¹

LAST Step Rounding Answer

∴

C v = 0.6581rad⁻¹

Vertical Tail Lift Curve Slope Formula Elements

Variables

Vertical Tail Lift Curve Slope

The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.

Symbol: C_v

Measurement: Reciprocal AngleUnit: rad⁻¹

Note: Value can be positive or negative.

Formulas to find Vertical Tail Lift Curve Slope

Vertical Tail Side Force

Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.

Symbol: Y_v

Measurement: ForceUnit: N

Note: Value can be positive or negative.

Formulas to find Vertical Tail Side Force

Vertical Tail Angle of Attack

Vertical Tail Angle of Attack is the angle of attack experienced by the vertical tailplane of an aircraft.

Symbol: α_v

Measurement: AngleUnit: rad

Note: Value can be positive or negative.

Formulas to find Vertical Tail Angle of Attack

Vertical Tail Dynamic Pressure

Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.

Symbol: Q_v

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Vertical Tail Dynamic Pressure

Vertical Tail Area

The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.

Symbol: S_v

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Vertical Tail Area

Other Formulas to find Vertical Tail Lift Curve Slope

Go Vertical Tail Lift Curve Slope for Given Moment

C v = \frac{N v}{𝒍 v \cdot (β + σ) \cdot Q v \cdot S v}

Go Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency

C v = \frac{C n}{V v \cdot η v \cdot (β + σ)}

Go Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient

C v = C n \cdot S \cdot b \cdot \frac{Q w}{𝒍 v \cdot S v \cdot Q v \cdot (β + σ)}

Other formulas in Vertical Tail Contribution category

Go Vertical Tail Angle of Attack

α v = σ + β

Go Vertical Tail Side Force

Y v = - C v \cdot α v \cdot S v \cdot Q v

Go Vertical Tail Angle of Attack for given Vertical Tail Side Force

α v = - (\frac{Y v}{C v \cdot Q v \cdot S v})

Go Vertical Tail Dynamic Pressure for given Vertical Tail Side Force

Q v = - (\frac{Y v}{C v \cdot α v \cdot S v})

How to Evaluate Vertical Tail Lift Curve Slope?

Vertical Tail Lift Curve Slope evaluator uses Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area)) to evaluate the Vertical Tail Lift Curve Slope, Vertical Tail Lift Curve Slope is a measure of the rate of change of vertical tail lift with respect to the angle of attack, which is essential in analyzing the stability and control of an aircraft during flight and is calculated by dividing the vertical tail side force by the product of the vertical tail angle of attack, dynamic pressure, and vertical tail area. Vertical Tail Lift Curve Slope is denoted by C_v symbol.

How to evaluate Vertical Tail Lift Curve Slope using this online evaluator? To use this online evaluator for Vertical Tail Lift Curve Slope, enter Vertical Tail Side Force (Y_v), Vertical Tail Angle of Attack (α_v), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) and hit the calculate button.

FAQs on Vertical Tail Lift Curve Slope

What is the formula to find Vertical Tail Lift Curve Slope?

The formula of Vertical Tail Lift Curve Slope is expressed as Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area)). Here is an example- 0.65812 = -((-4.235)/(0.117*11*5)).

How to calculate Vertical Tail Lift Curve Slope?

With Vertical Tail Side Force (Y_v), Vertical Tail Angle of Attack (α_v), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) we can find Vertical Tail Lift Curve Slope using the formula - Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area)).

What are the other ways to Calculate Vertical Tail Lift Curve Slope?

Here are the different ways to Calculate Vertical Tail Lift Curve Slope-

Vertical Tail Lift Curve Slope=Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area)
Vertical Tail Lift Curve Slope=Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Efficiency*(Sideslip Angle+Sidewash Angle))
Vertical Tail Lift Curve Slope=Yawing Moment Coefficient*Reference Area*Wingspan*Wing Dynamic Pressure/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*(Sideslip Angle+Sidewash Angle))

Can the Vertical Tail Lift Curve Slope be negative?

Yes, the Vertical Tail Lift Curve Slope, measured in Reciprocal Angle can be negative.

Which unit is used to measure Vertical Tail Lift Curve Slope?

Vertical Tail Lift Curve Slope is usually measured using the 1 per Radian[rad⁻¹] for Reciprocal Angle. 1 per Degree[rad⁻¹], 1 per Minute[rad⁻¹], 1 per Quadrant[rad⁻¹] are the few other units in which Vertical Tail Lift Curve Slope can be measured.

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Vertical Tail Lift Curve Slope Formula

​GoVertical Tail Lift Curve Slope for Given Moment Formula

​GoVertical Tail Lift Curve Slope for given Vertical Tail Efficiency Formula

Vertical Tail Lift Curve Slope Example

Vertical Tail Lift Curve Slope Solution

Vertical Tail Lift Curve Slope Formula Elements

Other Formulas to find Vertical Tail Lift Curve Slope

Other formulas in Vertical Tail Contribution category

How to Evaluate Vertical Tail Lift Curve Slope?

FAQs on Vertical Tail Lift Curve Slope

Variable Name

GoVertical Tail Lift Curve Slope for Given Moment Formula

GoVertical Tail Lift Curve Slope for given Vertical Tail Efficiency Formula