Wing Area for given Vertical Tail Volume Ratio Calculator

✖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 [S_v]			+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%
✖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.ⓘ Wing Area for given Vertical Tail Volume Ratio [S]

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Formula

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Wing Area for given Vertical Tail Volume Ratio

Formula

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

Example

`"5.11509m²"="1.2m"*"5m²"/("1.15m"*"1.02")`

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Wing Area for given Vertical Tail Volume Ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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 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.
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 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.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment Arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required
Wingspan: 1.15 Meter --> 1.15 Meter No Conversion Required
Vertical Tail Volume Ratio: 1.02 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S = 𝒍_v*S_v/(b*V_v) --> 1.2*5/(1.15*1.02)

Evaluating ... ...

S = 5.1150895140665

STEP 3: Convert Result to Output's Unit

5.1150895140665 Square Meter --> No Conversion Required

FINAL ANSWER

5.1150895140665 ≈ 5.11509 Square Meter <-- Reference 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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< 12 Wing-Tail Interaction Calculators

Wingspan for Yawing Moment Coefficient given Sideslip Angle and Sidewash Angle

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

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient

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

Dynamic Pressure at Wing for given Yawing Moment Coefficient

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

Wing Area for given Yawing Moment Coefficient

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

Vertical Tail Dynamic Pressure for given Moment

Go Vertical Tail Dynamic Pressure = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Area)

Wing Area for given Vertical Tail Volume Ratio

Go Reference Area = Vertical Tail Moment Arm*Vertical Tail Area/(Wingspan*Vertical Tail Volume Ratio)

Wingspan for given Vertical Tail Volume Ratio

Go Wingspan = Vertical Tail Moment Arm*Vertical Tail Area/(Reference Area*Vertical Tail Volume Ratio)

Wing Dynamic Pressure for given Yawing Moment Coefficient

Go Wing Dynamic Pressure = Vertical Tail Moment/(Yawing Moment Coefficient*Reference Area*Wingspan)

Wing Area for given Moment Produced by Vertical Tail

Go Reference Area = Vertical Tail Moment/(Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan)

Wingspan for given Yawing Moment Coefficient

Go Wingspan = Vertical Tail Moment/(Yawing Moment Coefficient*Reference Area*Wing Dynamic Pressure)

Dynamic Pressure at Vertical Tail for given Vertical Tail Efficiency

Go Vertical Tail Dynamic Pressure = Vertical Tail Efficiency*Wing Dynamic Pressure

Dynamic Pressure at Wing for given Vertical Tail Efficiency

Go Wing Dynamic Pressure = Vertical Tail Dynamic Pressure/Vertical Tail Efficiency

Wing Area for given Vertical Tail Volume Ratio Formula

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

How do you find wing area?

In aerodynamics, the surface area of a wing is calculated by looking at the wing from a top-down view and measuring the wing area. This surface area is also known as the planform area. The planform area is an important value when calculating the performance of an airplane.

How to Calculate Wing Area for given Vertical Tail Volume Ratio?

Wing Area for given Vertical Tail Volume Ratio calculator uses Reference Area = Vertical Tail Moment Arm*Vertical Tail Area/(Wingspan*Vertical Tail Volume Ratio) to calculate the Reference Area, Wing Area for given Vertical Tail Volume Ratio is a measure of the reference area of an aircraft's wing required for directional stability, calculated by considering the vertical tail moment arm, vertical tail area, wingspan, and vertical tail volume ratio, ensuring stable and controlled flight dynamics. Reference Area is denoted by S symbol.

How to calculate Wing Area for given Vertical Tail Volume Ratio using this online calculator? To use this online calculator for Wing Area for given Vertical Tail Volume Ratio, enter Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Wingspan (b) & Vertical Tail Volume Ratio (V_v) and hit the calculate button. Here is how the Wing Area for given Vertical Tail Volume Ratio calculation can be explained with given input values -> 5.11509 = 1.2*5/(1.15*1.02).

FAQ

What is Wing Area for given Vertical Tail Volume Ratio?

Wing Area for given Vertical Tail Volume Ratio is a measure of the reference area of an aircraft's wing required for directional stability, calculated by considering the vertical tail moment arm, vertical tail area, wingspan, and vertical tail volume ratio, ensuring stable and controlled flight dynamics and is represented as S = 𝒍_v*S_v/(b*V_v) or Reference Area = Vertical Tail Moment Arm*Vertical Tail Area/(Wingspan*Vertical Tail Volume Ratio). The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip & 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.

How to calculate Wing Area for given Vertical Tail Volume Ratio?

Wing Area for given Vertical Tail Volume Ratio is a measure of the reference area of an aircraft's wing required for directional stability, calculated by considering the vertical tail moment arm, vertical tail area, wingspan, and vertical tail volume ratio, ensuring stable and controlled flight dynamics is calculated using Reference Area = Vertical Tail Moment Arm*Vertical Tail Area/(Wingspan*Vertical Tail Volume Ratio). To calculate Wing Area for given Vertical Tail Volume Ratio, you need Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Wingspan (b) & Vertical Tail Volume Ratio (V_v). With our tool, you need to enter the respective value for Vertical Tail Moment Arm, Vertical Tail Area, Wingspan & Vertical Tail Volume Ratio 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 Reference Area?

In this formula, Reference Area uses Vertical Tail Moment Arm, Vertical Tail Area, Wingspan & Vertical Tail Volume Ratio. We can use 2 other way(s) to calculate the same, which is/are as follows -

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

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