Wing Area for given Moment Produced by Vertical Tail Calculator

✖Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Vertical Tail Moment [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%
✖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 [b]			+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 Moment Produced by Vertical Tail [S]

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Formula

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Wing Area for given Moment Produced by Vertical Tail

Formula

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

Example

`"5.081875m²"="5.4N*m"/("1.4"*"0.66Pa"*"1.15m")`

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Wing Area for given Moment Produced by Vertical Tail Solution

STEP 0: Pre-Calculation Summary

Formula Used

Reference Area = Vertical Tail Moment/(Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan)
S = N_v/(C_n*Q_w*b)
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 - (Measured in Newton Meter) - Vertical Tail Moment 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.
Wing Dynamic Pressure - (Measured in Pascal) - Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.
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.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 Newton Meter No Conversion Required
Yawing Moment Coefficient: 1.4 --> No Conversion Required
Wing Dynamic Pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Wingspan: 1.15 Meter --> 1.15 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S = N_v/(C_n*Q_w*b) --> 5.4/(1.4*0.66*1.15)

Evaluating ... ...

S = 5.08187464709204

STEP 3: Convert Result to Output's Unit

5.08187464709204 Square Meter --> No Conversion Required

FINAL ANSWER

5.08187464709204 ≈ 5.081875 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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PSG College of Technology (PSGCT), Coimbatore

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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 Moment Produced by Vertical Tail Formula

Reference Area = Vertical Tail Moment/(Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan)
S = N_v/(C_n*Q_w*b)

What is the best wing shape?

The elliptical wing is aerodynamically most efficient because the elliptical spanwise lift distribution induces the lowest possible drag.

How to Calculate Wing Area for given Moment Produced by Vertical Tail?

Wing Area for given Moment Produced by Vertical Tail calculator uses Reference Area = Vertical Tail Moment/(Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan) to calculate the Reference Area, Wing Area for given Moment Produced by Vertical Tail is a measure of the required area of the vertical tail to produce a specific yawing moment, dependent on the yawing moment coefficient, dynamic pressure, and wingspan of the aircraft. Reference Area is denoted by S symbol.

How to calculate Wing Area for given Moment Produced by Vertical Tail using this online calculator? To use this online calculator for Wing Area for given Moment Produced by Vertical Tail, enter Vertical Tail Moment (N_v), Yawing Moment Coefficient (C_n), Wing Dynamic Pressure (Q_w) & Wingspan (b) and hit the calculate button. Here is how the Wing Area for given Moment Produced by Vertical Tail calculation can be explained with given input values -> 5.081875 = 5.4/(1.4*0.66*1.15).

FAQ

What is Wing Area for given Moment Produced by Vertical Tail?

Wing Area for given Moment Produced by Vertical Tail is a measure of the required area of the vertical tail to produce a specific yawing moment, dependent on the yawing moment coefficient, dynamic pressure, and wingspan of the aircraft and is represented as S = N_v/(C_n*Q_w*b) or Reference Area = Vertical Tail Moment/(Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan). Vertical Tail Moment 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, Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft & The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

How to calculate Wing Area for given Moment Produced by Vertical Tail?

Wing Area for given Moment Produced by Vertical Tail is a measure of the required area of the vertical tail to produce a specific yawing moment, dependent on the yawing moment coefficient, dynamic pressure, and wingspan of the aircraft is calculated using Reference Area = Vertical Tail Moment/(Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan). To calculate Wing Area for given Moment Produced by Vertical Tail, you need Vertical Tail Moment (N_v), Yawing Moment Coefficient (C_n), Wing Dynamic Pressure (Q_w) & Wingspan (b). With our tool, you need to enter the respective value for Vertical Tail Moment, Yawing Moment Coefficient, Wing Dynamic Pressure & Wingspan 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, Yawing Moment Coefficient, Wing Dynamic Pressure & Wingspan. We can use 2 other way(s) to calculate the same, which is/are as follows -

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

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