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Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Formula

GoVertical Tail Dynamic Pressure for given Moment 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 = C n \cdot S \cdot b \cdot \frac{Q w}{𝒍 v \cdot S v \cdot C v \cdot (β + σ)}

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

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Example

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

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

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

10.985 = 1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 0.7 \cdot (0.05 + 0.067)}

10.985Pa = 1.4 \cdot 5.08m² \cdot 1.15m \cdot \frac{0.66Pa}{1.2m \cdot 5m² \cdot 0.7rad⁻¹ \cdot (0.05rad + 0.067rad)}

10.985 = 1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 0.7 \cdot (0.05 + 0.067)}

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Aircraft Mechanics » fx Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

Q v = 1.4 \cdot 5.08m² \cdot 1.15m \cdot \frac{0.66Pa}{1.2m \cdot 5m² \cdot 0.7rad⁻¹ \cdot (0.05rad + 0.067rad)}

Next Step Prepare to Evaluate

∴

Q v = 1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 0.7 \cdot (0.05 + 0.067)}

Next Step Evaluate

∴

Q v = 10.9849572649573Pa

LAST Step Rounding Answer

∴

Q v = 10.985Pa

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient 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

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

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

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 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 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

Other Formulas to find Vertical Tail Dynamic Pressure

Go Vertical Tail Dynamic Pressure for given Moment

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

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 Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient?

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient evaluator uses 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)) to evaluate the Vertical Tail Dynamic Pressure, Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient is a measure of the pressure exerted on the vertical tail of an aircraft, influenced by the yawing moment coefficient, reference area, wingspan, wing dynamic pressure and other factors, which affects the stability and control of the aircraft during flight. Vertical Tail Dynamic Pressure is denoted by Q_v symbol.

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

FAQs on Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient

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

The formula of Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient is expressed as 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)). Here is an example- 10.98496 = 1.4*5.08*1.15*0.66/(1.2*5*0.7*(0.05+0.067)).

How to calculate Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient?

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

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

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

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

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

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient 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 Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient can be measured.

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Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Formula

​GoVertical Tail Dynamic Pressure for given Moment Formula

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

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Example

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Solution

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Formula Elements

Other Formulas to find Vertical Tail Dynamic Pressure

Other formulas in Wing Tail Interaction category

How to Evaluate Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient?

FAQs on Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient

Variable Name

GoVertical Tail Dynamic Pressure for given Moment Formula

GoDynamic Pressure at Vertical Tail for given Vertical Tail Efficiency Formula