Sideslip 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%
✖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 [σ]			+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 for given Moment Produced by Vertical Tail [β]

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Sideslip Angle for given Moment Produced by Vertical Tail Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
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.

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
Sidewash Angle: 0.067 Radian --> 0.067 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

β = (N_v/(𝒍_v*C_v*Q_v*S_v))-σ --> (5.4/(1.2*0.7*11*5))-0.067

Evaluating ... ...

β = 0.0498831168831169

STEP 3: Convert Result to Output's Unit

0.0498831168831169 Radian --> No Conversion Required

FINAL ANSWER

0.0498831168831169 ≈ 0.049883 Radian <-- Sideslip Angle

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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National Institute Of Technology (NIT), Hamirpur

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< 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

Sideslip Angle for given Moment Produced by Vertical Tail Formula

LaTeX Go

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

What is a skid in aviation?

Skid is an aerodynamic condition, during a turn, where the tail of an aeroplane moves away from the centre of the turn or tends to follow a path which is outside that followed by the nose.

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

Sideslip Angle for given Moment Produced by Vertical Tail calculator uses Sideslip Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sidewash Angle to calculate the Sideslip Angle, Sideslip Angle for Given Moment Produced by Vertical Tail is a measure of the angle between the aircraft's forward motion and the direction it is pointing, calculated by considering the moment produced by the vertical tail, vertical tail moment arm, lift curve slope, dynamic pressure and area, while also taking into account the sidewash angle. Sideslip Angle is denoted by β symbol.

How to calculate Sideslip Angle for given Moment Produced by Vertical Tail using this online calculator? To use this online calculator for Sideslip 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) & Sidewash Angle (σ) and hit the calculate button. Here is how the Sideslip Angle for given Moment Produced by Vertical Tail calculation can be explained with given input values -> 0.049883 = (5.4/(1.2*0.7*11*5))-0.067.

FAQ

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

Sideslip Angle for Given Moment Produced by Vertical Tail is a measure of the angle between the aircraft's forward motion and the direction it is pointing, calculated by considering the moment produced by the vertical tail, vertical tail moment arm, lift curve slope, dynamic pressure and area, while also taking into account the sidewash angle and is represented as β = (N_v/(𝒍_v*C_v*Q_v*S_v))-σ or Sideslip Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sidewash 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 & 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.

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

Sideslip Angle for Given Moment Produced by Vertical Tail is a measure of the angle between the aircraft's forward motion and the direction it is pointing, calculated by considering the moment produced by the vertical tail, vertical tail moment arm, lift curve slope, dynamic pressure and area, while also taking into account the sidewash angle is calculated using Sideslip Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sidewash Angle. To calculate Sideslip 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) & Sidewash Angle (σ). 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 & Sidewash 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 Sideslip Angle?

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

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

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