Vertical Tail Moment Arm for Given Yawing Moment Coefficient Calculator

✖Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.ⓘ Yawing Moment Coefficient [C_n]			+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%
✖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 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%
✖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 [σ]			+10% -10%
✖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.ⓘ Reference Area [S]			+10% -10%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+10% -10%
✖Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing Dynamic Pressure [Q_w]			+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 for Given Yawing Moment Coefficient [𝒍_v]

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Vertical Tail Moment Arm for Given Yawing Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Moment Arm = Yawing Moment Coefficient/(Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Wing Dynamic Pressure))
𝒍_v = C_n/(S_v*Q_v*C_v*(β+σ)/(S*b*Q_w))
This formula uses 10 Variables

Variables Used

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.
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.
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.
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 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.
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.
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.
Reference Area - (Measured in Square Meter) - 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.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
Wing Dynamic Pressure - (Measured in Pascal) - Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Yawing Moment Coefficient: 1.4 --> No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical Tail Lift Curve Slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Sideslip Angle: 0.05 Radian --> 0.05 Radian No Conversion Required
Sidewash Angle: 0.067 Radian --> 0.067 Radian No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 1.15 Meter --> 1.15 Meter No Conversion Required
Wing Dynamic Pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

𝒍_v = C_n/(S_v*Q_v*C_v*(β+σ)/(S*b*Q_w)) --> 1.4/(5*11*0.7*(0.05+0.067)/(5.08*1.15*0.66))

Evaluating ... ...

𝒍_v = 1.19835897435897

STEP 3: Convert Result to Output's Unit

1.19835897435897 Meter --> No Conversion Required

FINAL ANSWER

1.19835897435897 ≈ 1.198359 Meter <-- Vertical Tail Moment Arm

(Calculation completed in 00.016 seconds)

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< Vertical Tail Contribution Calculators

Vertical Tail Angle of Attack for given Vertical Tail Side Force

LaTeX Go Vertical Tail Angle of Attack = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))

Vertical Tail Lift Curve Slope

LaTeX Go Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area))

Vertical Tail Side Force

LaTeX Go Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure

Vertical Tail Angle of Attack

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

Vertical Tail Moment Arm for Given Yawing Moment Coefficient Formula

LaTeX Go

How do planes turn?

Turning the control wheel clockwise raises the right aileron and lowers the left aileron, which rolls the aircraft to the right. The rudder works to control the yaw of the plane. The pilot moves rudder left and right, with left and right pedals. Used together, the rudder and the ailerons are used to turn the aircraft.

How to Calculate Vertical Tail Moment Arm for Given Yawing Moment Coefficient?

Vertical Tail Moment Arm for Given Yawing Moment Coefficient calculator uses Vertical Tail Moment Arm = Yawing Moment Coefficient/(Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Wing Dynamic Pressure)) to calculate the Vertical Tail Moment Arm, Vertical Tail Moment Arm for Given Yawing Moment Coefficient is a measure of the distance from the vertical tail's aerodynamic center to the aircraft's center of gravity, calculated by considering the yawing moment coefficient, vertical tail area, dynamic pressure, lift curve slope, sideslip angle, and other factors that influence the tail's effectiveness in stabilizing the aircraft's direction. Vertical Tail Moment Arm is denoted by 𝒍_v symbol.

How to calculate Vertical Tail Moment Arm for Given Yawing Moment Coefficient using this online calculator? To use this online calculator for Vertical Tail Moment Arm for Given Yawing Moment Coefficient, enter Yawing Moment Coefficient (C_n), 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. Here is how the Vertical Tail Moment Arm for Given Yawing Moment Coefficient calculation can be explained with given input values -> 1.201381 = 1.4/(5*11*0.7*(0.05+0.067)/(5.08*1.15*0.66)).

FAQ

What is Vertical Tail Moment Arm for Given Yawing Moment Coefficient?

Vertical Tail Moment Arm for Given Yawing Moment Coefficient is a measure of the distance from the vertical tail's aerodynamic center to the aircraft's center of gravity, calculated by considering the yawing moment coefficient, vertical tail area, dynamic pressure, lift curve slope, sideslip angle, and other factors that influence the tail's effectiveness in stabilizing the aircraft's direction and is represented as 𝒍_v = C_n/(S_v*Q_v*C_v*(β+σ)/(S*b*Q_w)) or Vertical Tail Moment Arm = Yawing Moment Coefficient/(Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Wing Dynamic Pressure)). Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft, The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, 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, 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, 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, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip & Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.

How to calculate Vertical Tail Moment Arm for Given Yawing Moment Coefficient?

Vertical Tail Moment Arm for Given Yawing Moment Coefficient is a measure of the distance from the vertical tail's aerodynamic center to the aircraft's center of gravity, calculated by considering the yawing moment coefficient, vertical tail area, dynamic pressure, lift curve slope, sideslip angle, and other factors that influence the tail's effectiveness in stabilizing the aircraft's direction is calculated using Vertical Tail Moment Arm = Yawing Moment Coefficient/(Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Wing Dynamic Pressure)). To calculate Vertical Tail Moment Arm for Given Yawing Moment Coefficient, you need Yawing Moment Coefficient (C_n), 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). With our tool, you need to enter the respective value for Yawing Moment Coefficient, Vertical Tail Area, Vertical Tail Dynamic Pressure, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle, Reference Area, Wingspan & Wing Dynamic Pressure 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 Vertical Tail Moment Arm?

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

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

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