Sidewash Angle for given Moment Produced by Vertical Tail Calculator

✖Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Vertical Tail Moment [N_v]			+10% -10%
✖The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.ⓘ Vertical Tail Moment Arm [𝒍_v]			+10% -10%
✖The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.ⓘ Vertical Tail Lift Curve Slope [C_v]			+10% -10%
✖Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical Tail Dynamic Pressure [Q_v]			+10% -10%
✖The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.ⓘ Vertical Tail Area [S_v]			+10% -10%
✖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.ⓘ Sideslip Angle [β]			+10% -10%

✖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.ⓘ Sidewash Angle for given Moment Produced by Vertical Tail [σ]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Aerodynamic Parameters Formulas PDF PDF Image

Sidewash Angle for given Moment Produced by Vertical Tail Solution

STEP 0: Pre-Calculation Summary

Formula Used

Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle
σ = (N_v/(𝒍_v*C_v*Q_v*S_v))-β
This formula uses 7 Variables

Variables Used

Sidewash Angle - (Measured in Radian) - 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.
Vertical Tail Moment - (Measured in Newton Meter) - Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
Vertical Tail Moment Arm - (Measured in Meter) - The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Vertical Tail Lift Curve Slope - (Measured in 1 per Radian) - The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.
Vertical Tail Dynamic Pressure - (Measured in Pascal) - Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.
Vertical Tail Area - (Measured in Square Meter) - The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.
Sideslip Angle - (Measured in Radian) - 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.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 Newton Meter No Conversion Required
Vertical Tail Moment Arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical Tail Lift Curve Slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required
Sideslip Angle: 0.05 Radian --> 0.05 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

σ = (N_v/(𝒍_v*C_v*Q_v*S_v))-β --> (5.4/(1.2*0.7*11*5))-0.05

Evaluating ... ...

σ = 0.0668831168831169

STEP 3: Convert Result to Output's Unit

0.0668831168831169 Radian --> No Conversion Required

FINAL ANSWER

0.0668831168831169 ≈ 0.066883 Radian <-- Sidewash Angle

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Aerospace » Aerodynamic Parameters » Sidewash Angle for given Moment Produced by Vertical Tail

Credits

Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< Aerodynamic Parameters Calculators

Sidewash Angle for given Moment Produced by Vertical Tail

LaTeX Go Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle

Yawing Moment Coefficient using Wingspan

LaTeX Go Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan)

Sideslip Angle for Aircraft

LaTeX Go Sideslip Angle = Vertical Tail Angle of Attack-Sidewash Angle

Sidewash angle

LaTeX Go Sidewash Angle = Vertical Tail Angle of Attack-Sideslip Angle

Sidewash Angle for given Moment Produced by Vertical Tail Formula

LaTeX Go

Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle
σ = (N_v/(𝒍_v*C_v*Q_v*S_v))-β

Why do airplanes Bank when they turn?

Airplanes bank when they turn because, in order to turn, there must be a force that will be exerted towards the center of a circle. By tilting the wings, the lift force on the wings has a non-vertical component that points toward the center of the curve, providing the centripetal force.

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

Sidewash Angle for given Moment Produced by Vertical Tail calculator 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 calculate 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 calculate Sidewash Angle for given Moment Produced by Vertical Tail using this online calculator? To use this online calculator 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. Here is how the Sidewash Angle for given Moment Produced by Vertical Tail calculation can be explained with given input values -> 0.066883 = (5.4/(1.2*0.7*11*5))-0.05.

FAQ

What is Sidewash Angle for given Moment Produced by Vertical Tail?

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 and is represented as σ = (N_v/(𝒍_v*C_v*Q_v*S_v))-β or Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle. Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft, The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline & 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.

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

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 is calculated using Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle. To calculate Sidewash Angle for given Moment Produced by Vertical Tail, you need 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). With our tool, you need to enter the respective value for Vertical Tail Moment, Vertical Tail Moment Arm, Vertical Tail Lift Curve Slope, Vertical Tail Dynamic Pressure, Vertical Tail Area & Sideslip Angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Sidewash Angle?

In this formula, Sidewash Angle uses Vertical Tail Moment, Vertical Tail Moment Arm, Vertical Tail Lift Curve Slope, Vertical Tail Dynamic Pressure, Vertical Tail Area & Sideslip Angle. We can use 3 other way(s) to calculate the same, which is/are as follows -

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

Home

FREE PDFs

🔍 Search