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Vertical Tail Moment Arm for given Lift Curve Slope Formula

GoVertical Tail Moment Arm for given Side Force Formula

GoVertical Tail Moment Arm for Given Yawing Moment Coefficient Formula

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The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft. Check FAQs

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

𝒍_v - Vertical Tail Moment Arm?N_v - Vertical Tail Moment?C_v - Vertical Tail Lift Curve Slope?β - Sideslip Angle?σ - Sidewash Angle?Q_v - Vertical Tail Dynamic Pressure?S_v - Vertical Tail Area?

Vertical Tail Moment Arm for given Lift Curve Slope Example

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Here is how the Vertical Tail Moment Arm for given Lift Curve Slope equation looks like with Values.

Here is how the Vertical Tail Moment Arm for given Lift Curve Slope equation looks like with Units.

Here is how the Vertical Tail Moment Arm for given Lift Curve Slope equation looks like.

1.1988 = \frac{5.4}{0.7 \cdot (0.05 + 0.067) \cdot 11 \cdot 5}

1.1988m = \frac{5.4N*m}{0.7rad⁻¹ \cdot (0.05rad + 0.067rad) \cdot 11Pa \cdot 5m²}

1.1988 = \frac{5.4}{0.7 \cdot (0.05 + 0.067) \cdot 11 \cdot 5}

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Vertical Tail Moment Arm for given Lift Curve Slope Solution

Follow our step by step solution on how to calculate Vertical Tail Moment Arm for given Lift Curve Slope?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

𝒍 v = \frac{5.4N*m}{0.7rad⁻¹ \cdot (0.05rad + 0.067rad) \cdot 11Pa \cdot 5m²}

Next Step Prepare to Evaluate

∴

𝒍 v = \frac{5.4}{0.7 \cdot (0.05 + 0.067) \cdot 11 \cdot 5}

Next Step Evaluate

∴

𝒍 v = 1.1988011988012m

LAST Step Rounding Answer

∴

𝒍 v = 1.1988m

Vertical Tail Moment Arm for given Lift Curve Slope Formula Elements

Variables

Vertical Tail Moment Arm

The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.

Symbol: 𝒍_v

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Vertical Tail Moment Arm

Vertical Tail Moment

Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.

Symbol: N_v

Measurement: Moment of ForceUnit: N*m

Note: Value can be positive or negative.

Formulas to find Vertical Tail Moment

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

Sideslip Angle

The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.

Symbol: β

Measurement: AngleUnit: rad

Note: Value can be positive or negative.

Formulas to find Sideslip Angle

Sidewash Angle

Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.

Symbol: σ

Measurement: AngleUnit: rad

Note: Value can be positive or negative.

Formulas to find Sidewash Angle

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 Moment Arm

Go Vertical Tail Moment Arm for given Side Force

𝒍 v = - \frac{N v}{Y v}

Go Vertical Tail Moment Arm for Given Yawing Moment Coefficient

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

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

How to Evaluate Vertical Tail Moment Arm for given Lift Curve Slope?

Vertical Tail Moment Arm for given Lift Curve Slope evaluator uses Vertical Tail Moment Arm = Vertical Tail Moment/(Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area) to evaluate the Vertical Tail Moment Arm, Vertical Tail Moment Arm for Given Lift Curve Slope is a measure of the distance from the aerodynamic center of the vertical tail to the axis of rotation, calculated by dividing the moment produced by the vertical tail by the product of the vertical tail lift curve slope, sideslip angle, sidewash angle, dynamic pressure, and vertical tail area. Vertical Tail Moment Arm is denoted by 𝒍_v symbol.

How to evaluate Vertical Tail Moment Arm for given Lift Curve Slope using this online evaluator? To use this online evaluator for Vertical Tail Moment Arm for given Lift Curve Slope, enter Vertical Tail Moment (N_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) and hit the calculate button.

FAQs on Vertical Tail Moment Arm for given Lift Curve Slope

What is the formula to find Vertical Tail Moment Arm for given Lift Curve Slope?

The formula of Vertical Tail Moment Arm for given Lift Curve Slope is expressed as Vertical Tail Moment Arm = Vertical Tail Moment/(Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area). Here is an example- 1.198801 = 5.4/(0.7*(0.05+0.067)*11*5).

How to calculate Vertical Tail Moment Arm for given Lift Curve Slope?

With Vertical Tail Moment (N_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) we can find Vertical Tail Moment Arm for given Lift Curve Slope using the formula - Vertical Tail Moment Arm = Vertical Tail Moment/(Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area).

What are the other ways to Calculate Vertical Tail Moment Arm?

Here are the different ways to Calculate Vertical Tail Moment Arm-

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

Can the Vertical Tail Moment Arm for given Lift Curve Slope be negative?

No, the Vertical Tail Moment Arm for given Lift Curve Slope, measured in Length cannot be negative.

Which unit is used to measure Vertical Tail Moment Arm for given Lift Curve Slope?

Vertical Tail Moment Arm for given Lift Curve Slope is usually measured using the Meter[m] for Length. Millimeter[m], Kilometer[m], Decimeter[m] are the few other units in which Vertical Tail Moment Arm for given Lift Curve Slope can be measured.

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Vertical Tail Moment Arm for given Lift Curve Slope Formula

​GoVertical Tail Moment Arm for given Side Force Formula

​GoVertical Tail Moment Arm for Given Yawing Moment Coefficient Formula

Vertical Tail Moment Arm for given Lift Curve Slope Example

Vertical Tail Moment Arm for given Lift Curve Slope Solution

Vertical Tail Moment Arm for given Lift Curve Slope Formula Elements

Other Formulas to find Vertical Tail Moment Arm

Other formulas in Vertical Tail Contribution category

How to Evaluate Vertical Tail Moment Arm for given Lift Curve Slope?

FAQs on Vertical Tail Moment Arm for given Lift Curve Slope

Variable Name

GoVertical Tail Moment Arm for given Side Force Formula

GoVertical Tail Moment Arm for Given Yawing Moment Coefficient Formula