FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Vertical Tail Area for given Yawing Moment Coefficient Formula

GoVertical Tail Area for given Vertical Tail Side Force Formula

GoVertical tail area for given vertical tail volume ratio Formula

Fx Copy

LaTeX Copy

The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline. Check FAQs

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

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

Vertical Tail Area for given Yawing Moment Coefficient Example

With values

With units

Only example

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

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

Here is how the Vertical Tail Area for given Yawing Moment Coefficient equation looks like.

4.9932 = 1.4 \cdot \frac{5.08 \cdot 1.15 \cdot 0.66}{1.2 \cdot 11 \cdot 0.7 \cdot (0.05 + 0.067)}

4.9932m² = 1.4 \cdot \frac{5.08m² \cdot 1.15m \cdot 0.66Pa}{1.2m \cdot 11Pa \cdot 0.7rad⁻¹ \cdot (0.05rad + 0.067rad)}

4.9932 = 1.4 \cdot \frac{5.08 \cdot 1.15 \cdot 0.66}{1.2 \cdot 11 \cdot 0.7 \cdot (0.05 + 0.067)}

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aircraft Mechanics » fx Vertical Tail Area for given Yawing Moment Coefficient

Vertical Tail Area for given Yawing Moment Coefficient Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

S v = 1.4 \cdot \frac{5.08m² \cdot 1.15m \cdot 0.66Pa}{1.2m \cdot 11Pa \cdot 0.7rad⁻¹ \cdot (0.05rad + 0.067rad)}

Next Step Prepare to Evaluate

∴

S v = 1.4 \cdot \frac{5.08 \cdot 1.15 \cdot 0.66}{1.2 \cdot 11 \cdot 0.7 \cdot (0.05 + 0.067)}

Next Step Evaluate

∴

S v = 4.99316239316239m²

LAST Step Rounding Answer

∴

S v = 4.9932m²

Vertical Tail Area for given Yawing Moment Coefficient Formula Elements

Variables

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

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 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

Other Formulas to find Vertical Tail Area

Go Vertical Tail Area for given Vertical Tail Side Force

S v = - \frac{Y v}{C v \cdot α v \cdot Q v}

Go Vertical tail area for given vertical tail volume ratio

S v = V v \cdot S \cdot \frac{b}{𝒍 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 Area for given Yawing Moment Coefficient?

Vertical Tail Area for given Yawing Moment Coefficient evaluator uses Vertical Tail Area = Yawing Moment Coefficient*(Reference Area*Wingspan*Wing Dynamic Pressure)/(Vertical Tail Moment Arm*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)) to evaluate the Vertical Tail Area, Vertical Tail Area for Given Yawing Moment Coefficient is a measure of the surface area of the vertical tail required to produce a given yawing moment coefficient, taking into account the reference area, wingspan, dynamic pressure, moment arm, and lift curve slope of the vertical tail, as well as the sideslip and sidewash angles, this calculation is crucial in aircraft design to ensure stability and control during flight. Vertical Tail Area is denoted by S_v symbol.

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

FAQs on Vertical Tail Area for given Yawing Moment Coefficient

What is the formula to find Vertical Tail Area for given Yawing Moment Coefficient?

The formula of Vertical Tail Area for given Yawing Moment Coefficient is expressed as Vertical Tail Area = Yawing Moment Coefficient*(Reference Area*Wingspan*Wing Dynamic Pressure)/(Vertical Tail Moment Arm*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)). Here is an example- 5.005754 = 1.4*(5.08*1.15*0.66)/(1.2*11*0.7*(0.05+0.067)).

How to calculate Vertical Tail Area 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 Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β) & Sidewash Angle (σ) we can find Vertical Tail Area for given Yawing Moment Coefficient using the formula - Vertical Tail Area = Yawing Moment Coefficient*(Reference Area*Wingspan*Wing Dynamic Pressure)/(Vertical Tail Moment Arm*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)).

What are the other ways to Calculate Vertical Tail Area?

Here are the different ways to Calculate Vertical Tail Area-

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

Can the Vertical Tail Area for given Yawing Moment Coefficient be negative?

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

Which unit is used to measure Vertical Tail Area for given Yawing Moment Coefficient?

Vertical Tail Area for given Yawing Moment Coefficient is usually measured using the Square Meter[m²] for Area. Square Kilometer[m²], Square Centimeter[m²], Square Millimeter[m²] are the few other units in which Vertical Tail Area for given Yawing Moment Coefficient can be measured.

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Vertical Tail Area for given Yawing Moment Coefficient Formula

​GoVertical Tail Area for given Vertical Tail Side Force Formula

​GoVertical tail area for given vertical tail volume ratio Formula

Vertical Tail Area for given Yawing Moment Coefficient Example

Vertical Tail Area for given Yawing Moment Coefficient Solution

Vertical Tail Area for given Yawing Moment Coefficient Formula Elements

Other Formulas to find Vertical Tail Area

Other formulas in Vertical Tail Contribution category

How to Evaluate Vertical Tail Area for given Yawing Moment Coefficient?

FAQs on Vertical Tail Area for given Yawing Moment Coefficient

Variable Name

GoVertical Tail Area for given Vertical Tail Side Force Formula

GoVertical tail area for given vertical tail volume ratio Formula