Vertical tail area for given vertical tail volume ratio Calculator

✖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.ⓘ Vertical Tail Volume Ratio [V_v]			+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%
✖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 Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.ⓘ Vertical tail area for given vertical tail volume ratio [S_v]

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Vertical tail area for given vertical tail volume ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Moment Arm
S_v = V_v*S*b/𝒍_v
This formula uses 5 Variables

Variables Used

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 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 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.

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 Moment Arm: 1.2 Meter --> 1.2 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S_v = V_v*S*b/𝒍_v --> 1.02*5.08*1.15/1.2

Evaluating ... ...

S_v = 4.9657

STEP 3: Convert Result to Output's Unit

4.9657 Square Meter --> No Conversion Required

FINAL ANSWER

4.9657 Square Meter <-- Vertical Tail Area

(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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< 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 area for given vertical tail volume ratio Formula

LaTeX Go

Vertical Tail Area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Moment Arm
S_v = V_v*S*b/𝒍_v

What is the advantage of T-Tail configuration?

This configuration also allows high-performance aerodynamics and an excellent glide ratio as the empennage is less affected by the wing and fuselage slipstream.

How to Calculate Vertical tail area for given vertical tail volume ratio?

Vertical tail area for given vertical tail volume ratio calculator uses Vertical Tail Area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Moment Arm to calculate the Vertical Tail Area, Vertical Tail Area for Given Vertical Tail Volume Ratio is a calculation that determines the vertical tail area of an aircraft based on the vertical tail volume ratio, reference area, wingspan, and vertical tail moment arm, this formula is essential in aircraft design, as it helps to ensure the stability and control of the aircraft during flight. Vertical Tail Area is denoted by S_v symbol.

How to calculate Vertical tail area for given vertical tail volume ratio using this online calculator? To use this online calculator for Vertical tail area for given vertical tail volume ratio, enter Vertical Tail Volume Ratio (V_v), Reference Area (S), Wingspan (b) & Vertical Tail Moment Arm (𝒍_v) and hit the calculate button. Here is how the Vertical tail area for given vertical tail volume ratio calculation can be explained with given input values -> 5.306483 = 1.02*5.08*1.15/1.2.

FAQ

What is Vertical tail area for given vertical tail volume ratio?

Vertical Tail Area for Given Vertical Tail Volume Ratio is a calculation that determines the vertical tail area of an aircraft based on the vertical tail volume ratio, reference area, wingspan, and vertical tail moment arm, this formula is essential in aircraft design, as it helps to ensure the stability and control of the aircraft during flight and is represented as S_v = V_v*S*b/𝒍_v or Vertical Tail Area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Moment Arm. 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 Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.

How to calculate Vertical tail area for given vertical tail volume ratio?

Vertical Tail Area for Given Vertical Tail Volume Ratio is a calculation that determines the vertical tail area of an aircraft based on the vertical tail volume ratio, reference area, wingspan, and vertical tail moment arm, this formula is essential in aircraft design, as it helps to ensure the stability and control of the aircraft during flight is calculated using Vertical Tail Area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Moment Arm. To calculate Vertical tail area for given vertical tail volume ratio, you need Vertical Tail Volume Ratio (V_v), Reference Area (S), Wingspan (b) & Vertical Tail Moment Arm (𝒍_v). With our tool, you need to enter the respective value for Vertical Tail Volume Ratio, Reference Area, Wingspan & Vertical Tail Moment Arm 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 Area?

In this formula, Vertical Tail Area uses Vertical Tail Volume Ratio, Reference Area, Wingspan & Vertical Tail Moment Arm. We can use 3 other way(s) to calculate the same, which is/are as follows -

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

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