Vertical Tail Moment Arm for given Vertical Tail Volume Ratio Solution

STEP 0: Pre-Calculation Summary
Formula Used
Vertical Tail Moment Arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Area
𝒍v = Vv*S*b/Sv
This formula uses 5 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 Volume Ratio - Vertical Tail Volume Ratio relates to the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's e.g., the wing area, and the wingspan.
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.
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 Volume Ratio: 1.02 --> 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
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
𝒍v = Vv*S*b/Sv --> 1.02*5.08*1.15/5
Evaluating ... ...
𝒍v = 1.191768
STEP 3: Convert Result to Output's Unit
1.191768 Meter --> No Conversion Required
FINAL ANSWER
1.191768 Meter <-- Vertical Tail Moment Arm
(Calculation completed in 00.004 seconds)

Credits

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Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
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Indian Institute of Technology (IIT), Bombay
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Vertical Tail Contribution Calculators

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​ 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 Vertical Tail Volume Ratio Formula

​LaTeX ​Go
Vertical Tail Moment Arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Area
𝒍v = Vv*S*b/Sv

Why is a T-tail configuration?

A T-tail is an empennage configuration in which the tailplane is mounted to the top of the fin. The arrangement looks like the capital letter T, hence the name.

How to Calculate Vertical Tail Moment Arm for given Vertical Tail Volume Ratio?

Vertical Tail Moment Arm for given Vertical Tail Volume Ratio calculator uses Vertical Tail Moment Arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Area to calculate the Vertical Tail Moment Arm, Vertical Tail Moment Arm for given Vertical Tail Volume Ratio is a measure of the distance from the aircraft's center of gravity to the vertical tail, calculated by multiplying the vertical tail volume ratio, reference area, and wingspan, and dividing by the vertical tail area, which is critical in determining the aircraft's stability and control during flight. Vertical Tail Moment Arm is denoted by 𝒍v symbol.

How to calculate Vertical Tail Moment Arm for given Vertical Tail Volume Ratio using this online calculator? To use this online calculator for Vertical Tail Moment Arm for given Vertical Tail Volume Ratio, enter Vertical Tail Volume Ratio (Vv), Reference Area (S), Wingspan (b) & Vertical Tail Area (Sv) and hit the calculate button. Here is how the Vertical Tail Moment Arm for given Vertical Tail Volume Ratio calculation can be explained with given input values -> 1.273556 = 1.02*5.08*1.15/5.

FAQ

What is Vertical Tail Moment Arm for given Vertical Tail Volume Ratio?
Vertical Tail Moment Arm for given Vertical Tail Volume Ratio is a measure of the distance from the aircraft's center of gravity to the vertical tail, calculated by multiplying the vertical tail volume ratio, reference area, and wingspan, and dividing by the vertical tail area, which is critical in determining the aircraft's stability and control during flight and is represented as 𝒍v = Vv*S*b/Sv or Vertical Tail Moment Arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Area. Vertical Tail Volume Ratio relates to the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's e.g., the wing area, and the wingspan, 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 & 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 Vertical Tail Volume Ratio?
Vertical Tail Moment Arm for given Vertical Tail Volume Ratio is a measure of the distance from the aircraft's center of gravity to the vertical tail, calculated by multiplying the vertical tail volume ratio, reference area, and wingspan, and dividing by the vertical tail area, which is critical in determining the aircraft's stability and control during flight is calculated using Vertical Tail Moment Arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Area. To calculate Vertical Tail Moment Arm for given Vertical Tail Volume Ratio, you need Vertical Tail Volume Ratio (Vv), Reference Area (S), Wingspan (b) & Vertical Tail Area (Sv). With our tool, you need to enter the respective value for Vertical Tail Volume Ratio, Reference Area, Wingspan & 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 Volume Ratio, Reference Area, Wingspan & 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 = Vertical Tail Moment/(Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area)
  • 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))
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