Dynamic Pressure at Wing for given Yawing Moment Coefficient Calculator

✖The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.ⓘ Vertical Tail Moment Arm [𝒍_v]			+10% -10%
✖The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.ⓘ Vertical Tail Area [S_v]			+10% -10%
✖Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical Tail Dynamic Pressure [Q_v]			+10% -10%
✖The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.ⓘ Vertical Tail Lift Curve Slope [C_v]			+10% -10%
✖The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.ⓘ Sideslip Angle [β]			+10% -10%
✖Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.ⓘ Sidewash Angle [σ]			+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%
✖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.ⓘ Dynamic Pressure at Wing for given Yawing Moment Coefficient [Q_w]

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Dynamic Pressure at Wing for given Yawing Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

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)
Q_w = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(S*b*C_n)
This formula uses 10 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 Arm - (Measured in Meter) - The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Vertical Tail Area - (Measured in Square Meter) - The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.
Vertical Tail Dynamic Pressure - (Measured in Pascal) - Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.
Vertical Tail Lift Curve Slope - (Measured in 1 per Radian) - The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.
Sideslip Angle - (Measured in Radian) - The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.
Sidewash Angle - (Measured in Radian) - Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment Arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical Tail Lift Curve Slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Sideslip Angle: 0.05 Radian --> 0.05 Radian No Conversion Required
Sidewash Angle: 0.067 Radian --> 0.067 Radian 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
Yawing Moment Coefficient: 1.4 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Q_w = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(S*b*C_n) --> 1.2*5*11*0.7*(0.05+0.067)/(5.08*1.15*1.4)

Evaluating ... ...

Q_w = 0.66090380006847

STEP 3: Convert Result to Output's Unit

0.66090380006847 Pascal --> No Conversion Required

FINAL ANSWER

0.66090380006847 ≈ 0.660904 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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< 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)

Dynamic Pressure at Wing for given Yawing Moment Coefficient Formula

LaTeX Go

How is the wingspan measured for an aircraft?

The wingspan of an aircraft is always measured in a straight line, from wingtip to wingtip, independently of wing shape or sweep.

How to Calculate Dynamic Pressure at Wing for given Yawing Moment Coefficient?

Dynamic Pressure at Wing for given Yawing Moment Coefficient calculator uses 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) to calculate the Wing Dynamic Pressure, Dynamic Pressure at Wing for given Yawing Moment Coefficient is a measure of the pressure exerted on an aircraft wing due to its velocity, taking into account the vertical tail's moment arm, area and lift curve slope, as well as the sideslip and sidewash angles, referenced to the wing's span and directional stability. Wing Dynamic Pressure is denoted by Q_w symbol.

How to calculate Dynamic Pressure at Wing for given Yawing Moment Coefficient using this online calculator? To use this online calculator for Dynamic Pressure at Wing for given Yawing Moment Coefficient, enter Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Reference Area (S), Wingspan (b) & Yawing Moment Coefficient (C_n) and hit the calculate button. Here is how the Dynamic Pressure at Wing for given Yawing Moment Coefficient calculation can be explained with given input values -> 0.659241 = 1.2*5*11*0.7*(0.05+0.067)/(5.08*1.15*1.4).

FAQ

What is Dynamic Pressure at Wing for given Yawing Moment Coefficient?

Dynamic Pressure at Wing for given Yawing Moment Coefficient is a measure of the pressure exerted on an aircraft wing due to its velocity, taking into account the vertical tail's moment arm, area and lift curve slope, as well as the sideslip and sidewash angles, referenced to the wing's span and directional stability and is represented as Q_w = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(S*b*C_n) or 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). The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft, The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind, Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane, 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 & Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.

How to calculate Dynamic Pressure at Wing for given Yawing Moment Coefficient?

How many ways are there to calculate Wing Dynamic Pressure?

In this formula, Wing Dynamic Pressure uses 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. We can use 2 other way(s) to calculate the same, which is/are as follows -

Wing Dynamic Pressure = Vertical Tail Moment/(Yawing Moment Coefficient*Reference Area*Wingspan)
Wing Dynamic Pressure = Vertical Tail Dynamic Pressure/Vertical Tail Efficiency

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