Wing Dynamic Pressure for given Yawing Moment Coefficient 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%
✖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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Wing Dynamic Pressure for given Yawing Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing Dynamic Pressure = Vertical Tail Moment/(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.
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.
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

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 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: 1.15 Meter --> 1.15 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Q_w = N_v/(C_n*S*b) --> 5.4/(1.4*5.08*1.15)

Evaluating ... ...

Q_w = 0.660243556511958

STEP 3: Convert Result to Output's Unit

0.660243556511958 Pascal --> No Conversion Required

FINAL ANSWER

0.660243556511958 ≈ 0.660244 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

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

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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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)

Wing Dynamic Pressure for given Yawing Moment Coefficient Formula

LaTeX Go

Wing Dynamic Pressure = Vertical Tail Moment/(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 = Vertical Tail Moment/(Yawing Moment Coefficient*Reference Area*Wingspan) to calculate the Wing Dynamic Pressure, Wing Dynamic Pressure for given Yawing Moment Coefficient is a measure of the pressure exerted on the wing of an aircraft, calculated by dividing the moment produced by the vertical tail by the product of the yawing moment coefficient, 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 Vertical Tail Moment (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 -> 0.660244 = 5.4/(1.4*5.08*1.15).

FAQ

What is Wing Dynamic Pressure for given Yawing Moment Coefficient?

Wing Dynamic Pressure for given Yawing Moment Coefficient is a measure of the pressure exerted on the wing of an aircraft, calculated by dividing the moment produced by the vertical tail by the product of the yawing moment coefficient, reference area and wingspan and is represented as Q_w = N_v/(C_n*S*b) or Wing Dynamic Pressure = Vertical Tail Moment/(Yawing Moment Coefficient*Reference Area*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, 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?

Wing Dynamic Pressure for given Yawing Moment Coefficient is a measure of the pressure exerted on the wing of an aircraft, calculated by dividing the moment produced by the vertical tail by the product of the yawing moment coefficient, reference area and wingspan is calculated using Wing Dynamic Pressure = Vertical Tail Moment/(Yawing Moment Coefficient*Reference Area*Wingspan). To calculate Wing Dynamic Pressure for given Yawing Moment Coefficient, you need Vertical Tail Moment (N_v), Yawing Moment Coefficient (C_n), Reference Area (S) & Wingspan (b). With our tool, you need to enter the respective value for Vertical Tail Moment, 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 Vertical Tail Moment, 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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