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Sidewash Angle for given Moment Produced by Vertical Tail Formula

GoSidewash angle Formula

GoSidewash Angle given Yawing Moment Coefficient using Wingspan Formula

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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. Check FAQs

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

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

Sidewash Angle for given Moment Produced by Vertical Tail Example

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Here is how the Sidewash Angle for given Moment Produced by Vertical Tail equation looks like with Values.

Here is how the Sidewash Angle for given Moment Produced by Vertical Tail equation looks like with Units.

Here is how the Sidewash Angle for given Moment Produced by Vertical Tail equation looks like.

0.0669 = (\frac{5.4}{1.2 \cdot 0.7 \cdot 11 \cdot 5}) - 0.05

0.0669rad = (\frac{5.4N*m}{1.2m \cdot 0.7rad⁻¹ \cdot 11Pa \cdot 5m²}) - 0.05rad

0.0669 = (\frac{5.4}{1.2 \cdot 0.7 \cdot 11 \cdot 5}) - 0.05

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Sidewash Angle for given Moment Produced by Vertical Tail Solution

Follow our step by step solution on how to calculate Sidewash Angle for given Moment Produced by Vertical Tail?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

σ = (\frac{5.4N*m}{1.2m \cdot 0.7rad⁻¹ \cdot 11Pa \cdot 5m²}) - 0.05rad

Next Step Prepare to Evaluate

∴

σ = (\frac{5.4}{1.2 \cdot 0.7 \cdot 11 \cdot 5}) - 0.05

Next Step Evaluate

∴

σ = 0.0668831168831169rad

LAST Step Rounding Answer

∴

σ = 0.0669rad

Sidewash Angle for given Moment Produced by Vertical Tail Formula Elements

Variables

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 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

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

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

Other Formulas to find Sidewash Angle

Go Sidewash angle

σ = α v - β

Go Sidewash Angle given Yawing Moment Coefficient using Wingspan

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

Other formulas in Aerodynamic Parameters category

Go Sideslip Angle for Aircraft

β = α v - σ

Go Yawing Moment Coefficient using Wingspan

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

How to Evaluate Sidewash Angle for given Moment Produced by Vertical Tail?

Sidewash Angle for given Moment Produced by Vertical Tail evaluator uses Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle to evaluate the Sidewash Angle, Sidewash Angle for Given Moment Produced by Vertical Tail is a measure of the angle between the vertical tail's force vector and its moment arm, calculated by considering the moment produced by the vertical tail, vertical tail moment arm, lift curve slope, dynamic pressure and area, while accounting for the sideslip angle, providing a critical value for aircraft stability and control analysis. Sidewash Angle is denoted by σ symbol.

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

FAQs on Sidewash Angle for given Moment Produced by Vertical Tail

What is the formula to find Sidewash Angle for given Moment Produced by Vertical Tail?

The formula of Sidewash Angle for given Moment Produced by Vertical Tail is expressed as Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle. Here is an example- 0.066883 = (5.4/(1.2*0.7*11*5))-0.05.

How to calculate Sidewash Angle for given Moment Produced by Vertical Tail?

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

What are the other ways to Calculate Sidewash Angle?

Here are the different ways to Calculate Sidewash Angle-

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

Can the Sidewash Angle for given Moment Produced by Vertical Tail be negative?

Yes, the Sidewash Angle for given Moment Produced by Vertical Tail, measured in Angle can be negative.

Which unit is used to measure Sidewash Angle for given Moment Produced by Vertical Tail?

Sidewash Angle for given Moment Produced by Vertical Tail is usually measured using the Radian[rad] for Angle. Degree[rad], Minute[rad], Second[rad] are the few other units in which Sidewash Angle for given Moment Produced by Vertical Tail can be measured.

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Sidewash Angle for given Moment Produced by Vertical Tail Formula

​GoSidewash angle Formula

​GoSidewash Angle given Yawing Moment Coefficient using Wingspan Formula

Sidewash Angle for given Moment Produced by Vertical Tail Example

Sidewash Angle for given Moment Produced by Vertical Tail Solution

Sidewash Angle for given Moment Produced by Vertical Tail Formula Elements

Other Formulas to find Sidewash Angle

Other formulas in Aerodynamic Parameters category

How to Evaluate Sidewash Angle for given Moment Produced by Vertical Tail?

FAQs on Sidewash Angle for given Moment Produced by Vertical Tail

Variable Name

GoSidewash angle Formula

GoSidewash Angle given Yawing Moment Coefficient using Wingspan Formula