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Vertical Tail Dynamic Pressure for given Moment Formula

GoDynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Formula

GoDynamic Pressure at Vertical Tail for given Vertical Tail Efficiency Formula

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

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

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

Vertical Tail Dynamic Pressure for given Moment Example

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Here is how the Vertical Tail Dynamic Pressure for given Moment equation looks like with Values.

Here is how the Vertical Tail Dynamic Pressure for given Moment equation looks like with Units.

Here is how the Vertical Tail Dynamic Pressure for given Moment equation looks like.

10.989 = \frac{5.4}{1.2 \cdot 0.7 \cdot (0.05 + 0.067) \cdot 5}

10.989Pa = \frac{5.4N*m}{1.2m \cdot 0.7rad⁻¹ \cdot (0.05rad + 0.067rad) \cdot 5m²}

10.989 = \frac{5.4}{1.2 \cdot 0.7 \cdot (0.05 + 0.067) \cdot 5}

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Vertical Tail Dynamic Pressure for given Moment Solution

Follow our step by step solution on how to calculate Vertical Tail Dynamic Pressure for given Moment?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

Q v = \frac{5.4N*m}{1.2m \cdot 0.7rad⁻¹ \cdot (0.05rad + 0.067rad) \cdot 5m²}

Next Step Prepare to Evaluate

∴

Q v = \frac{5.4}{1.2 \cdot 0.7 \cdot (0.05 + 0.067) \cdot 5}

Next Step Evaluate

∴

Q v = 10.989010989011Pa

LAST Step Rounding Answer

∴

Q v = 10.989Pa

Vertical Tail Dynamic Pressure for given Moment Formula Elements

Variables

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 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

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 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 Dynamic Pressure

Go Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient

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

Go Dynamic Pressure at Vertical Tail for given Vertical Tail Efficiency

Q v = η v \cdot Q w

Other formulas in Wing Tail Interaction category

Go Wing Dynamic Pressure for given Yawing Moment Coefficient

Q w = \frac{N v}{C n \cdot S \cdot b}

Go Wing Area for given Moment Produced by Vertical Tail

S = \frac{N v}{C n \cdot Q w \cdot b}

How to Evaluate Vertical Tail Dynamic Pressure for given Moment?

Vertical Tail Dynamic Pressure for given Moment evaluator uses Vertical Tail Dynamic Pressure = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Area) to evaluate the Vertical Tail Dynamic Pressure, Vertical Tail Dynamic Pressure for given Moment is a measure of the pressure exerted by the vertical tail of an aircraft on the surrounding air, calculated by dividing the moment produced by the vertical tail by the product of the vertical tail moment arm, lift curve slope, sideslip angle, sidewash angle, and vertical tail area, providing a critical indicator of aircraft stability and control. Vertical Tail Dynamic Pressure is denoted by Q_v symbol.

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

FAQs on Vertical Tail Dynamic Pressure for given Moment

What is the formula to find Vertical Tail Dynamic Pressure for given Moment?

The formula of Vertical Tail Dynamic Pressure for given Moment is expressed as Vertical Tail Dynamic Pressure = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Area). Here is an example- 10.98901 = 5.4/(1.2*0.7*(0.05+0.067)*5).

How to calculate Vertical Tail Dynamic Pressure for given Moment?

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

What are the other ways to Calculate Vertical Tail Dynamic Pressure?

Here are the different ways to Calculate Vertical Tail Dynamic Pressure-

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

Can the Vertical Tail Dynamic Pressure for given Moment be negative?

No, the Vertical Tail Dynamic Pressure for given Moment, measured in Pressure cannot be negative.

Which unit is used to measure Vertical Tail Dynamic Pressure for given Moment?

Vertical Tail Dynamic Pressure for given Moment is usually measured using the Pascal[Pa] for Pressure. Kilopascal[Pa], Bar[Pa], Pound Per Square Inch[Pa] are the few other units in which Vertical Tail Dynamic Pressure for given Moment can be measured.

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Vertical Tail Dynamic Pressure for given Moment Formula

​GoDynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Formula

​GoDynamic Pressure at Vertical Tail for given Vertical Tail Efficiency Formula

Vertical Tail Dynamic Pressure for given Moment Example

Vertical Tail Dynamic Pressure for given Moment Solution

Vertical Tail Dynamic Pressure for given Moment Formula Elements

Other Formulas to find Vertical Tail Dynamic Pressure

Other formulas in Wing Tail Interaction category

How to Evaluate Vertical Tail Dynamic Pressure for given Moment?

FAQs on Vertical Tail Dynamic Pressure for given Moment

Variable Name

GoDynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Formula

GoDynamic Pressure at Vertical Tail for given Vertical Tail Efficiency Formula