Wing area for given moment produced by vertical tail Calculator

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Static Stability and Control

Aircraft Design

Aircraft Performance

Introduction and Governing Equations

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Directional Stability

Longitudinal 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%
✖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

`"0.04329m²"="2N*m"/("1.4"*"0.66Pa"*"50m")`

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Wing area for given moment produced by vertical tail Solution

STEP 0: Pre-Calculation Summary

Formula Used

Reference Area = Moment produced by vertical tail/(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.
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.
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

Moment produced by vertical tail: 2 Newton Meter --> 2 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: 50 Meter --> 50 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S = N_v/(C_n*Q_w*b) --> 2/(1.4*0.66*50)

Evaluating ... ...

S = 0.0432900432900433

STEP 3: Convert Result to Output's Unit

0.0432900432900433 Square Meter --> No Conversion Required

FINAL ANSWER

0.0432900432900433 ≈ 0.04329 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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< 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

Wing area for given moment produced by vertical tail Formula

Reference Area = Moment produced by vertical tail/(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 = Moment produced by vertical tail/(Yawing moment coefficient*Wing dynamic pressure*Wingspan) to calculate the Reference Area, The Wing area for given moment produced by vertical tail is the projected area of the planform and is bounded by the leading and trailing edges and the wing tips. 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 Moment produced by vertical tail (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 -> 0.04329 = 2/(1.4*0.66*50).

FAQ

What is Wing area for given moment produced by vertical tail?

The Wing area for given moment produced by vertical tail is the projected area of the planform and is bounded by the leading and trailing edges and the wing tips and is represented as S = N_v/(C_n*Q_w*b) or Reference Area = Moment produced by vertical tail/(Yawing moment coefficient*Wing dynamic pressure*Wingspan). 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, 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?

The Wing area for given moment produced by vertical tail is the projected area of the planform and is bounded by the leading and trailing edges and the wing tips is calculated using Reference Area = Moment produced by vertical tail/(Yawing moment coefficient*Wing dynamic pressure*Wingspan). To calculate Wing area for given moment produced by vertical tail, you need Moment produced by vertical tail (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 Moment produced by vertical tail, 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 Moment produced by vertical tail, 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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