Wingspan 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 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%
✖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 Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan for given Vertical Tail Volume Ratio [b]

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Wingspan for given Vertical Tail Volume Ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
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 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
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Vertical Tail Volume Ratio: 1.02 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

b = 𝒍_v*S_v/(S*V_v) --> 1.2*5/(5.08*1.02)

Evaluating ... ...

b = 1.15794349235757

STEP 3: Convert Result to Output's Unit

1.15794349235757 Meter --> No Conversion Required

FINAL ANSWER

1.15794349235757 ≈ 1.157943 Meter <-- Wingspan

(Calculation completed in 00.020 seconds)

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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 Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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< Wing Tail Interaction Calculators

Wingspan for Yawing Moment Coefficient given Sideslip Angle and Sidewash Angle

LaTeX 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)

Wing Dynamic Pressure for given Yawing Moment Coefficient

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

Wing Area for given Moment Produced by Vertical Tail

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

Wingspan for given Yawing Moment Coefficient

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

Wingspan for given Vertical Tail Volume Ratio Formula

LaTeX Go

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

What is the disadvantage of a T-tail?

A T-tail aircraft may be prone to suffering a dangerous deep stall condition, where a stalled wing at high angles of attack may blank the airflow over the tailplane and elevators, thereby leading to loss of pitch control.

How to Calculate Wingspan for given Vertical Tail Volume Ratio?

Wingspan for given Vertical Tail Volume Ratio calculator uses Wingspan = Vertical Tail Moment Arm*Vertical Tail Area/(Reference Area*Vertical Tail Volume Ratio) to calculate the Wingspan, Wingspan for given Vertical Tail Volume Ratio is a measure of the wingspan of an aircraft, calculated by dividing the product of the vertical tail moment arm and vertical tail area by the product of the reference area and the vertical tail volume ratio, providing a critical design parameter for aircraft stability and control. Wingspan is denoted by b symbol.

How to calculate Wingspan for given Vertical Tail Volume Ratio using this online calculator? To use this online calculator for Wingspan for given Vertical Tail Volume Ratio, enter Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Reference Area (S) & Vertical Tail Volume Ratio (V_v) and hit the calculate button. Here is how the Wingspan for given Vertical Tail Volume Ratio calculation can be explained with given input values -> 1.157943 = 1.2*5/(5.08*1.02).

FAQ

What is Wingspan for given Vertical Tail Volume Ratio?

Wingspan for given Vertical Tail Volume Ratio is a measure of the wingspan of an aircraft, calculated by dividing the product of the vertical tail moment arm and vertical tail area by the product of the reference area and the vertical tail volume ratio, providing a critical design parameter for aircraft stability and control and is represented as b = 𝒍_v*S_v/(S*V_v) or Wingspan = Vertical Tail Moment Arm*Vertical Tail Area/(Reference Area*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 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 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 Wingspan for given Vertical Tail Volume Ratio?

Wingspan for given Vertical Tail Volume Ratio is a measure of the wingspan of an aircraft, calculated by dividing the product of the vertical tail moment arm and vertical tail area by the product of the reference area and the vertical tail volume ratio, providing a critical design parameter for aircraft stability and control is calculated using Wingspan = Vertical Tail Moment Arm*Vertical Tail Area/(Reference Area*Vertical Tail Volume Ratio). To calculate Wingspan for given Vertical Tail Volume Ratio, you need Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Reference Area (S) & Vertical Tail Volume Ratio (V_v). With our tool, you need to enter the respective value for Vertical Tail Moment Arm, Vertical Tail Area, Reference Area & 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 Wingspan?

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

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

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