Wing Area 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%
✖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 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 [Q_w]			+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 Yawing Moment Coefficient [S]

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Wing Area for given Yawing Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

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)
S = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(C_n*b*Q_w)
This formula uses 10 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 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.
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.
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.
Wing Dynamic Pressure - (Measured in Pascal) - Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.

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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(C_n*b*Q_w) --> 1.2*5*11*0.7*(0.05+0.067)/(1.4*1.15*0.66)

Evaluating ... ...

S = 5.08695652173913

STEP 3: Convert Result to Output's Unit

5.08695652173913 Square Meter --> No Conversion Required

FINAL ANSWER

5.08695652173913 ≈ 5.086957 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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< 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 Area for given Yawing Moment Coefficient Formula

LaTeX Go

Which is better high wing or low wing?

High wing airplanes are very stable at slower speeds, meaning they can right themselves quickly if they encounter turbulence while traveling slowly. Low-wing airplanes are more stable than mid-wing airplanes, but not as much as high-wing airplanes. They are also more maneuverable than high-wing airplanes.

How to Calculate Wing Area for given Yawing Moment Coefficient?

Wing Area for given Yawing Moment Coefficient calculator uses 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) to calculate the Reference Area, Wing Area for given Yawing Moment Coefficient is a calculation of the reference area required for directional stability, taking into account the vertical tail moment arm, area, and dynamic pressure, as well as the wing's lift curve slope, sideslip angle, and sidewash angle, all in relation to the yawing moment coefficient and wingspan, this formula is crucial in aerodynamics to ensure stable flight conditions. Reference Area is denoted by S symbol.

How to calculate Wing Area for given Yawing Moment Coefficient using this online calculator? To use this online calculator for Wing Area 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), Yawing Moment Coefficient (C_n), Wingspan (b) & Wing Dynamic Pressure (Q_w) and hit the calculate button. Here is how the Wing Area for given Yawing Moment Coefficient calculation can be explained with given input values -> 5.086957 = 1.2*5*11*0.7*(0.05+0.067)/(1.4*1.15*0.66).

FAQ

What is Wing Area for given Yawing Moment Coefficient?

Wing Area for given Yawing Moment Coefficient is a calculation of the reference area required for directional stability, taking into account the vertical tail moment arm, area, and dynamic pressure, as well as the wing's lift curve slope, sideslip angle, and sidewash angle, all in relation to the yawing moment coefficient and wingspan, this formula is crucial in aerodynamics to ensure stable flight conditions and is represented as S = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(C_n*b*Q_w) or 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). 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, Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip & Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.

How to calculate Wing Area for given Yawing Moment Coefficient?

Wing Area for given Yawing Moment Coefficient is a calculation of the reference area required for directional stability, taking into account the vertical tail moment arm, area, and dynamic pressure, as well as the wing's lift curve slope, sideslip angle, and sidewash angle, all in relation to the yawing moment coefficient and wingspan, this formula is crucial in aerodynamics to ensure stable flight conditions is calculated using 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). To calculate Wing Area for given Yawing Moment Coefficient, you need 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), Yawing Moment Coefficient (C_n), Wingspan (b) & Wing Dynamic Pressure (Q_w). With our tool, you need to enter the respective value for 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 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 Arm, Vertical Tail Area, Vertical Tail Dynamic Pressure, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle, Yawing Moment Coefficient, Wingspan & Wing Dynamic Pressure. We can use 2 other way(s) to calculate the same, which is/are as follows -

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

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