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Vertical Tail Moment Arm for Given Yawing Moment Coefficient Formula

GoVertical Tail Moment Arm for given Side Force Formula

GoVertical Tail Moment Arm for given Lift Curve Slope 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{C n}{S v \cdot Q v \cdot C v \cdot \frac{β + σ}{S \cdot b \cdot Q w}}

𝒍_v - Vertical Tail Moment Arm?C_n - Yawing Moment Coefficient?S_v - Vertical Tail Area?Q_v - Vertical Tail Dynamic Pressure?C_v - Vertical Tail Lift Curve Slope?β - Sideslip Angle?σ - Sidewash Angle?S - Reference Area?b - Wingspan?Q_w - Wing Dynamic Pressure?

Vertical Tail Moment Arm for Given Yawing Moment Coefficient Example

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Here is how the Vertical Tail Moment Arm for Given Yawing Moment Coefficient equation looks like with Values.

Here is how the Vertical Tail Moment Arm for Given Yawing Moment Coefficient equation looks like with Units.

Here is how the Vertical Tail Moment Arm for Given Yawing Moment Coefficient equation looks like.

1.1984 = \frac{1.4}{5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 0.66}}

1.1984m = \frac{1.4}{5m² \cdot 11Pa \cdot 0.7rad⁻¹ \cdot \frac{0.05rad + 0.067rad}{5.08m² \cdot 1.15m \cdot 0.66Pa}}

1.1984 = \frac{1.4}{5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 0.66}}

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Vertical Tail Moment Arm for Given Yawing Moment Coefficient Solution

Follow our step by step solution on how to calculate Vertical Tail Moment Arm for Given Yawing Moment Coefficient?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

𝒍 v = \frac{1.4}{5m² \cdot 11Pa \cdot 0.7rad⁻¹ \cdot \frac{0.05rad + 0.067rad}{5.08m² \cdot 1.15m \cdot 0.66Pa}}

Next Step Prepare to Evaluate

∴

𝒍 v = \frac{1.4}{5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 0.66}}

Next Step Evaluate

∴

𝒍 v = 1.19835897435897m

LAST Step Rounding Answer

∴

𝒍 v = 1.1984m

Vertical Tail Moment Arm for Given Yawing Moment Coefficient 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

Yawing Moment Coefficient

Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.

Symbol: C_n

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Yawing Moment Coefficient

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

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 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

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

Wingspan

The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

Symbol: b

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Wingspan

Wing Dynamic Pressure

Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.

Symbol: Q_w

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Wing Dynamic Pressure

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 Lift Curve Slope

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

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 Yawing Moment Coefficient?

Vertical Tail Moment Arm for Given Yawing Moment Coefficient evaluator uses 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)) to evaluate the Vertical Tail Moment Arm, Vertical Tail Moment Arm for Given Yawing Moment Coefficient is a measure of the distance from the vertical tail's aerodynamic center to the aircraft's center of gravity, calculated by considering the yawing moment coefficient, vertical tail area, dynamic pressure, lift curve slope, sideslip angle, and other factors that influence the tail's effectiveness in stabilizing the aircraft's direction. Vertical Tail Moment Arm is denoted by 𝒍_v symbol.

How to evaluate Vertical Tail Moment Arm for Given Yawing Moment Coefficient using this online evaluator? To use this online evaluator for Vertical Tail Moment Arm for Given Yawing Moment Coefficient, enter Yawing Moment Coefficient (C_n), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Reference Area (S), Wingspan (b) & Wing Dynamic Pressure (Q_w) and hit the calculate button.

FAQs on Vertical Tail Moment Arm for Given Yawing Moment Coefficient

What is the formula to find Vertical Tail Moment Arm for Given Yawing Moment Coefficient?

The formula of Vertical Tail Moment Arm for Given Yawing Moment Coefficient is expressed as 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)). Here is an example- 1.201381 = 1.4/(5*11*0.7*(0.05+0.067)/(5.08*1.15*0.66)).

How to calculate Vertical Tail Moment Arm for Given Yawing Moment Coefficient?

With Yawing Moment Coefficient (C_n), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Reference Area (S), Wingspan (b) & Wing Dynamic Pressure (Q_w) we can find Vertical Tail Moment Arm for Given Yawing Moment Coefficient using the formula - 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)).

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

Can the Vertical Tail Moment Arm for Given Yawing Moment Coefficient be negative?

No, the Vertical Tail Moment Arm for Given Yawing Moment Coefficient, measured in Length cannot be negative.

Which unit is used to measure Vertical Tail Moment Arm for Given Yawing Moment Coefficient?

Vertical Tail Moment Arm for Given Yawing Moment Coefficient 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 Yawing Moment Coefficient can be measured.

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Vertical Tail Moment Arm for Given Yawing Moment Coefficient Formula

​GoVertical Tail Moment Arm for given Side Force Formula

​GoVertical Tail Moment Arm for given Lift Curve Slope Formula

Vertical Tail Moment Arm for Given Yawing Moment Coefficient Example

Vertical Tail Moment Arm for Given Yawing Moment Coefficient Solution

Vertical Tail Moment Arm for Given Yawing Moment Coefficient 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 Yawing Moment Coefficient?

FAQs on Vertical Tail Moment Arm for Given Yawing Moment Coefficient

Variable Name

GoVertical Tail Moment Arm for given Side Force Formula

GoVertical Tail Moment Arm for given Lift Curve Slope Formula