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Vertical Tail Lift Curve Slope for Given Moment Formula

GoVertical Tail Lift Curve Slope 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{N v}{𝒍 v \cdot (β + σ) \cdot Q v \cdot S v}

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

Vertical Tail Lift Curve Slope for Given Moment Example

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

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

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

0.6993 = \frac{5.4}{1.2 \cdot (0.05 + 0.067) \cdot 11 \cdot 5}

0.6993rad⁻¹ = \frac{5.4N*m}{1.2m \cdot (0.05rad + 0.067rad) \cdot 11Pa \cdot 5m²}

0.6993 = \frac{5.4}{1.2 \cdot (0.05 + 0.067) \cdot 11 \cdot 5}

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Vertical Tail Lift Curve Slope for Given Moment Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

C v = \frac{5.4N*m}{1.2m \cdot (0.05rad + 0.067rad) \cdot 11Pa \cdot 5m²}

Next Step Prepare to Evaluate

∴

C v = \frac{5.4}{1.2 \cdot (0.05 + 0.067) \cdot 11 \cdot 5}

Next Step Evaluate

∴

C v = 0.699300699300699rad⁻¹

LAST Step Rounding Answer

∴

C v = 0.6993rad⁻¹

Vertical Tail Lift Curve Slope for Given Moment 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 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 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

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 Lift Curve Slope

Go Vertical Tail Lift Curve Slope

C v = - (\frac{Y v}{α v \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)}

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 Lift Curve Slope for Given Moment?

Vertical Tail Lift Curve Slope for Given Moment evaluator uses Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area) to evaluate the Vertical Tail Lift Curve Slope, Vertical Tail Lift Curve Slope for Given Moment is a measure of the rate of change of lift force exerted by the vertical tail of an aircraft in response to sideslip and sidewash angles, which is critical for stability and control during flight, it is a fundamental concept in aerodynamics and aircraft design, helping engineers to optimize the vertical tail's performance and ensure safe and efficient flight operations. Vertical Tail Lift Curve Slope is denoted by C_v symbol.

How to evaluate Vertical Tail Lift Curve Slope for Given Moment using this online evaluator? To use this online evaluator for Vertical Tail Lift Curve Slope for Given Moment, enter Vertical Tail Moment (N_v), Vertical Tail Moment Arm (𝒍_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 Lift Curve Slope for Given Moment

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

The formula of Vertical Tail Lift Curve Slope for Given Moment is expressed as Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area). Here is an example- 0.699301 = 5.4/(1.2*(0.05+0.067)*11*5).

How to calculate Vertical Tail Lift Curve Slope for Given Moment?

With Vertical Tail Moment (N_v), Vertical Tail Moment Arm (𝒍_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) we can find Vertical Tail Lift Curve Slope for Given Moment using the formula - Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*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 Side Force/(Vertical Tail Angle of Attack*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 for Given Moment be negative?

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

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

Vertical Tail Lift Curve Slope for Given Moment 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 for Given Moment can be measured.

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Vertical Tail Lift Curve Slope for Given Moment Formula

​GoVertical Tail Lift Curve Slope Formula

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

Vertical Tail Lift Curve Slope for Given Moment Example

Vertical Tail Lift Curve Slope for Given Moment Solution

Vertical Tail Lift Curve Slope for Given Moment 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 for Given Moment?

FAQs on Vertical Tail Lift Curve Slope for Given Moment

Variable Name

GoVertical Tail Lift Curve Slope Formula

GoVertical Tail Lift Curve Slope for given Vertical Tail Efficiency Formula