FormulaDen.com

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

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Formula

GoYawing Moment Coefficient using Wingspan Formula

GoYawing Moment Coefficient for given Vertical Tail Volume Ratio Formula

Fx Copy

LaTeX Copy

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

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

C_n - Yawing Moment Coefficient?𝒍_v - Vertical Tail Moment Arm?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?

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Example

With values

With units

Only example

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

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

Here is how the Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope equation looks like.

1.4019 = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 0.66}

1.4019 = 1.2m \cdot 5m² \cdot 11Pa \cdot 0.7rad⁻¹ \cdot \frac{0.05rad + 0.067rad}{5.08m² \cdot 1.15m \cdot 0.66Pa}

1.4019 = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 0.66}

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 Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

C n = 1.2m \cdot 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

∴

C n = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 0.66}

Next Step Evaluate

∴

C n = 1.40191715166039

LAST Step Rounding Answer

∴

C n = 1.4019

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Formula Elements

Variables

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 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 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 Yawing Moment Coefficient

Go Yawing Moment Coefficient using Wingspan

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

Go Yawing Moment Coefficient for given Vertical Tail Volume Ratio

C n = V v \cdot η v \cdot C v \cdot (β + σ)

Other formulas in Aerodynamic Parameters category

Go Sideslip Angle for Aircraft

β = α v - σ

Go Sidewash angle

σ = α v - β

How to Evaluate Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope?

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope evaluator uses Yawing Moment Coefficient = Vertical Tail Moment Arm*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 Yawing Moment Coefficient, Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope is a measure of the rotational force that causes an aircraft to turn around its vertical axis, influenced by the vertical tail's moment arm, area, dynamic pressure, lift curve slope, sideslip angle, and sidewash angle, relative to the wing's reference area, span, and dynamic pressure. Yawing Moment Coefficient is denoted by C_n symbol.

How to evaluate Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope using this online evaluator? To use this online evaluator for Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope, enter Vertical Tail Moment Arm (𝒍_v), 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 Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope

What is the formula to find Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope?

The formula of Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope is expressed as Yawing Moment Coefficient = Vertical Tail Moment Arm*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- 1.401917 = 1.2*5*11*0.7*(0.05+0.067)/(5.08*1.15*0.66).

How to calculate Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope?

With Vertical Tail Moment Arm (𝒍_v), 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 Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope using the formula - Yawing Moment Coefficient = Vertical Tail Moment Arm*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 Yawing Moment Coefficient?

Here are the different ways to Calculate Yawing Moment Coefficient-

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

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Formula

​GoYawing Moment Coefficient using Wingspan Formula

​GoYawing Moment Coefficient for given Vertical Tail Volume Ratio Formula

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Example

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Solution

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Formula Elements

Other Formulas to find Yawing Moment Coefficient

Other formulas in Aerodynamic Parameters category

How to Evaluate Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope?

FAQs on Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope

Variable Name

GoYawing Moment Coefficient using Wingspan Formula

GoYawing Moment Coefficient for given Vertical Tail Volume Ratio Formula