Wing dynamic pressure for given yawing moment coefficient 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%
✖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%
✖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%

✖Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing dynamic pressure for given yawing moment coefficient [Q_w]

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Formula

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Wing dynamic pressure for given yawing moment coefficient

Formula

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

Example

`"0.005624Pa"="2N*m"/("1.4"*"5.08m²"*"50m")`

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Wing dynamic pressure for given yawing moment coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing dynamic pressure = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wingspan)
Q_w = N_v/(C_n*S*b)
This formula uses 5 Variables

Variables Used

Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.
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.
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
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 50 Meter --> 50 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Q_w = N_v/(C_n*S*b) --> 2/(1.4*5.08*50)

Evaluating ... ...

Q_w = 0.00562429696287964

STEP 3: Convert Result to Output's Unit

0.00562429696287964 Pascal --> No Conversion Required

FINAL ANSWER

0.00562429696287964 ≈ 0.005624 Pascal <-- Wing dynamic pressure

(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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< 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 dynamic pressure for given yawing moment coefficient Formula

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

Does dynamic pressure increase with velocity?

The dynamic pressure is a defined property of a moving flow of gas. The dynamic pressure increases because of the increasing velocity to some maximum value called the maximum dynamic pressure. Then the dynamic pressure decreases because of the decreasing density.

How to Calculate Wing dynamic pressure for given yawing moment coefficient?

Wing dynamic pressure for given yawing moment coefficient calculator uses Wing dynamic pressure = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wingspan) to calculate the Wing dynamic pressure, The wing dynamic pressure for given yawing moment coefficient is a function of the moment produced by vertical tail, wing reference area, and wingspan. Wing dynamic pressure is denoted by Q_w symbol.

How to calculate Wing dynamic pressure for given yawing moment coefficient using this online calculator? To use this online calculator for Wing dynamic pressure for given yawing moment coefficient, enter Moment produced by vertical tail (N_v), Yawing moment coefficient (C_n), Reference Area (S) & Wingspan (b) and hit the calculate button. Here is how the Wing dynamic pressure for given yawing moment coefficient calculation can be explained with given input values -> 0.005624 = 2/(1.4*5.08*50).

FAQ

What is Wing dynamic pressure for given yawing moment coefficient?

The wing dynamic pressure for given yawing moment coefficient is a function of the moment produced by vertical tail, wing reference area, and wingspan and is represented as Q_w = N_v/(C_n*S*b) or Wing dynamic pressure = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*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, 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 & 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 dynamic pressure for given yawing moment coefficient?

The wing dynamic pressure for given yawing moment coefficient is a function of the moment produced by vertical tail, wing reference area, and wingspan is calculated using Wing dynamic pressure = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wingspan). To calculate Wing dynamic pressure for given yawing moment coefficient, you need Moment produced by vertical tail (N_v), Yawing moment coefficient (C_n), Reference Area (S) & Wingspan (b). With our tool, you need to enter the respective value for Moment produced by vertical tail, Yawing moment coefficient, Reference Area & 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 Wing dynamic pressure?

In this formula, Wing dynamic pressure uses Moment produced by vertical tail, Yawing moment coefficient, Reference Area & Wingspan. We can use 2 other way(s) to calculate the same, which is/are as follows -

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 dynamic pressure = Vertical tail dynamic pressure/Vertical tail efficiency

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