Vertical Tail Moment Arm for given Lift Curve Slope 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 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%
✖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 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 Lift Curve Slope [𝒍_v]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Vertical Tail Contribution Formulas PDF PDF Image

Vertical Tail Moment Arm for given Lift Curve Slope Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 Newton Meter 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
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

𝒍_v = N_v/(C_v*(β+σ)*Q_v*S_v) --> 5.4/(0.7*(0.05+0.067)*11*5)

Evaluating ... ...

𝒍_v = 1.1988011988012

STEP 3: Convert Result to Output's Unit

1.1988011988012 Meter --> No Conversion Required

FINAL ANSWER

1.1988011988012 ≈ 1.198801 Meter <-- Vertical Tail Moment Arm

(Calculation completed in 00.008 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Aerospace » Vertical Tail Contribution » Vertical Tail Moment Arm for given Lift Curve Slope

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!

< 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 Lift Curve Slope Formula

LaTeX Go

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

What aircraft design feature gives an aircraft longitudinal stability?

Thrust line affects longitudinal stability. Power or thrust can also have a destabilizing effect in that an increase of power may tend to make the nose rise. The aircraft designer can offset this by establishing a “high thrust line” wherein the line of thrust passes above the CG.

How to Calculate Vertical Tail Moment Arm for given Lift Curve Slope?

Vertical Tail Moment Arm for given Lift Curve Slope calculator uses Vertical Tail Moment Arm = Vertical Tail Moment/(Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area) to calculate the Vertical Tail Moment Arm, Vertical Tail Moment Arm for Given Lift Curve Slope is a measure of the distance from the aerodynamic center of the vertical tail to the axis of rotation, calculated by dividing the moment produced by the vertical tail by the product of the vertical tail lift curve slope, sideslip angle, sidewash angle, dynamic pressure, and vertical tail area. Vertical Tail Moment Arm is denoted by 𝒍_v symbol.

How to calculate Vertical Tail Moment Arm for given Lift Curve Slope using this online calculator? To use this online calculator for Vertical Tail Moment Arm for given Lift Curve Slope, enter Vertical Tail Moment (N_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) and hit the calculate button. Here is how the Vertical Tail Moment Arm for given Lift Curve Slope calculation can be explained with given input values -> 1.198801 = 5.4/(0.7*(0.05+0.067)*11*5).

FAQ

What is Vertical Tail Moment Arm for given Lift Curve Slope?

Vertical Tail Moment Arm for Given Lift Curve Slope is a measure of the distance from the aerodynamic center of the vertical tail to the axis of rotation, calculated by dividing the moment produced by the vertical tail by the product of the vertical tail lift curve slope, sideslip angle, sidewash angle, dynamic pressure, and vertical tail area and is represented as 𝒍_v = N_v/(C_v*(β+σ)*Q_v*S_v) or 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 is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, 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, 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.

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

Vertical Tail Moment Arm for Given Lift Curve Slope is a measure of the distance from the aerodynamic center of the vertical tail to the axis of rotation, calculated by dividing the moment produced by the vertical tail by the product of the vertical tail lift curve slope, sideslip angle, sidewash angle, dynamic pressure, and vertical tail area is calculated using Vertical Tail Moment Arm = Vertical Tail Moment/(Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area). To calculate Vertical Tail Moment Arm for given Lift Curve Slope, you need Vertical Tail Moment (N_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v). With our tool, you need to enter the respective value for Vertical Tail Moment, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle, Vertical Tail Dynamic Pressure & Vertical Tail Area 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 Vertical Tail Moment, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle, Vertical Tail Dynamic Pressure & Vertical Tail Area. 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 = 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))
Vertical Tail Moment Arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Area

Home

FREE PDFs

🔍 Search