Wingspan for given yawing moment coefficient Calculator

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Static Stability and Control

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Introduction and Governing Equations

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Directional Stability

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Wing-Tail Interaction

Aerodynamic Parameters

Vertical Tail Contribution

✖The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Moment produced by vertical tail [N_v]			+10% -10%
✖Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.ⓘ Yawing moment coefficient [C_n]			+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%
✖Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing dynamic pressure [Q_w]			+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 yawing moment coefficient [b]

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Formula

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Wingspan for given yawing moment coefficient

Formula

`"b" = "N"_{"v"}/("C"_{"n"}*"S"*"Q"_{"w"})`

Example

`"0.426083m"="2N*m"/("1.4"*"5.08m²"*"0.66Pa")`

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Wingspan for given yawing moment coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wingspan = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wing dynamic pressure)
b = N_v/(C_n*S*Q_w)
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.
Moment produced by vertical tail - (Measured in Newton Meter) - The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
Yawing moment coefficient - Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.
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.
Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Moment produced by vertical tail: 2 Newton Meter --> 2 Newton Meter No Conversion Required
Yawing moment coefficient: 1.4 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wing dynamic pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

b = N_v/(C_n*S*Q_w) --> 2/(1.4*5.08*0.66)

Evaluating ... ...

b = 0.426083103248458

STEP 3: Convert Result to Output's Unit

0.426083103248458 Meter --> No Conversion Required

FINAL ANSWER

0.426083103248458 ≈ 0.426083 Meter <-- Wingspan

(Calculation completed in 00.004 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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< 13 Wing-Tail Interaction Calculators

Sideslip angle for given yawing moment coefficient

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

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

Wing dynamic pressure for given yawing moment coefficient

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

Wing area for given moment produced by vertical tail

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

Wingspan for given yawing moment coefficient

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

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)

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

Wingspan for given yawing moment coefficient Formula

Wingspan = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wing dynamic pressure)
b = N_v/(C_n*S*Q_w)

What is the world's largest airplane by wingspan?

The Stratolaunch is the world's largest aircraft. Its 385-foot wingspan is longer than a football field.

How to Calculate Wingspan for given yawing moment coefficient?

Wingspan for given yawing moment coefficient calculator uses Wingspan = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wing dynamic pressure) to calculate the Wingspan, The Wingspan for given yawing moment coefficient is the distance from the tip of one wing of a bird or airplane to the tip of the other wing. Wingspan is denoted by b symbol.

How to calculate Wingspan for given yawing moment coefficient using this online calculator? To use this online calculator for Wingspan for given yawing moment coefficient, enter Moment produced by vertical tail (N_v), Yawing moment coefficient (C_n), Reference Area (S) & Wing dynamic pressure (Q_w) and hit the calculate button. Here is how the Wingspan for given yawing moment coefficient calculation can be explained with given input values -> 0.426083 = 2/(1.4*5.08*0.66).

FAQ

What is Wingspan for given yawing moment coefficient?

The Wingspan for given yawing moment coefficient is the distance from the tip of one wing of a bird or airplane to the tip of the other wing and is represented as b = N_v/(C_n*S*Q_w) or Wingspan = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wing dynamic pressure). The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, 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 dynamic pressure is the dynamic pressure associated with the wing of an aircraft.

How to calculate Wingspan for given yawing moment coefficient?

The Wingspan for given yawing moment coefficient is the distance from the tip of one wing of a bird or airplane to the tip of the other wing is calculated using Wingspan = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wing dynamic pressure). To calculate Wingspan for given yawing moment coefficient, you need Moment produced by vertical tail (N_v), Yawing moment coefficient (C_n), Reference Area (S) & Wing dynamic pressure (Q_w). With our tool, you need to enter the respective value for Moment produced by vertical tail, Yawing moment coefficient, Reference Area & Wing dynamic pressure 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 Moment produced by vertical tail, Yawing moment coefficient, Reference Area & Wing dynamic pressure. We can use 2 other way(s) to calculate the same, which is/are as follows -

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

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