Vertical tail area for given vertical tail volume ratio Calculator

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Static Stability and Control

Aircraft Design

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Introduction and Governing Equations

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Directional Stability

Longitudinal Stability

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Vertical Tail Contribution

Aerodynamic Parameters

Wing-Tail Interaction

✖Vertical Tail Volume Ratio relates the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.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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Formula

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Vertical tail area for given vertical tail volume ratio

Formula

`"S"_{"v"} = "V"_{"v"}*"S"*"b"/"𝒍"_{"v"}`

Example

`"317.5m²"="1.5"*"5.08m²"*"50m"/"1.2m"`

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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 the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.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: 1.5 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 50 Meter --> 50 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 --> 1.5*5.08*50/1.2

Evaluating ... ...

S_v = 317.5

STEP 3: Convert Result to Output's Unit

317.5 Square Meter --> No Conversion Required

FINAL ANSWER

317.5 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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Verified by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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< 24 Vertical Tail Contribution Calculators

Vertical tail moment arm for given yawing moment coefficient

Go 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 area for given yawing moment coefficient

Go 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 lift curve slope for given yawing moment coefficient

Go Vertical tail Lift curve slope = Yawing moment coefficient*Reference Area*Wingspan*Wing dynamic pressure/(Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*(Sideslip angle+Sidewash angle))

Vertical tail moment arm for given lift curve slope

Go Vertical tail moment arm = Moment produced by vertical tail/(Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area)

Vertical tail lift curve slope for given moment

Go Vertical tail Lift curve slope = Moment produced by vertical tail/(Vertical tail moment arm*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area)

Vertical tail area for given moment

Go Vertical tail area = Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure)

Moment produced by vertical tail for given lift curve slope

Go Moment produced by vertical tail = Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area

Vertical tail lift curve slope for given yawing moment coefficient and Vertical Tail Efficiency

Go Vertical tail Lift curve slope = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*(Sideslip angle+Sidewash angle))

Vertical tail volume ratio for given yawing moment coefficient

Go Vertical Tail Volume Ratio = Yawing moment coefficient/(Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))

Vertical tail efficiency for given yawing moment coefficient

Go Vertical tail efficiency = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))

Vertical tail area for given vertical tail side force

Go Vertical tail area = -(Vertical Tail Side Force) /(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail dynamic pressure)

Vertical tail dynamic pressure for given vertical tail side force

Go Vertical tail dynamic pressure = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area)

Vertical tail angle of attack for given vertical tail side force

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

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

Go Vertical Tail Side Force = -Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area*Vertical tail dynamic pressure

Moment produced by vertical tail for given moment coefficient

Go Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area

Vertical tail volume ratio

Go Vertical Tail Volume Ratio = Vertical tail moment arm*Vertical tail area/(Reference Area*Wingspan)

Vertical tail moment arm for given vertical tail volume ratio

Go Vertical tail moment arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail area

Vertical tail area for given vertical tail volume ratio

Go Vertical tail area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail moment arm

Vertical tail moment arm for given side force

Go Vertical tail moment arm = -Moment produced by vertical tail/Vertical Tail Side Force

Moment produced by vertical tail for given side force

Go Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force

Vertical tail side force for given moment

Go Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm

Vertical tail efficiency

Go Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure

Vertical tail angle of attack

Go Vertical tail angle of attack = Sidewash angle+Sideslip angle

Vertical tail area for given vertical tail volume ratio Formula

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, The Vertical tail area for given vertical tail volume ratio is dependent on vertical tail moment arm, wing reference area, and wingspan. 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 -> 317.5 = 1.5*5.08*50/1.2.

FAQ

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

The Vertical tail area for given vertical tail volume ratio is dependent on vertical tail moment arm, wing reference area, and wingspan 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 the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.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?

The Vertical tail area for given vertical tail volume ratio is dependent on vertical tail moment arm, wing reference area, and wingspan 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 = Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure)

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