Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope 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%
✖Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing Dynamic Pressure [Q_w]			+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 for given Vertical Tail Lift Curve Slope [C_n]

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Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Solution

STEP 0: Pre-Calculation Summary

Formula Used

Yawing Moment Coefficient = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Wing Dynamic Pressure)
C_n = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(S*b*Q_w)
This formula uses 10 Variables

Variables Used

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.
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.
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
Reference Area: 5.08 Square Meter --> 5.08 Square Meter 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

C_n = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(S*b*Q_w) --> 1.2*5*11*0.7*(0.05+0.067)/(5.08*1.15*0.66)

Evaluating ... ...

C_n = 1.40191715166039

STEP 3: Convert Result to Output's Unit

1.40191715166039 --> No Conversion Required

FINAL ANSWER

1.40191715166039 ≈ 1.401917 <-- Yawing Moment Coefficient

(Calculation completed in 00.004 seconds)

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< Aerodynamic Parameters Calculators

Sidewash Angle for given Moment Produced by Vertical Tail

LaTeX Go Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle

Yawing Moment Coefficient using Wingspan

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

Sideslip Angle for Aircraft

LaTeX Go Sideslip Angle = Vertical Tail Angle of Attack-Sidewash Angle

Sidewash angle

LaTeX Go Sidewash Angle = Vertical Tail Angle of Attack-Sideslip Angle

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope Formula

LaTeX Go

Which force is responsible for yawing moment?

The yawing motion is being caused by the deflection of the rudder of the aircraft. The rudder is a hinged section at the rear of the vertical stabilizer.

How to Calculate Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope?

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope calculator uses Yawing Moment Coefficient = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Wing Dynamic Pressure) to calculate the Yawing Moment Coefficient, Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope is a measure of the rotational force that causes an aircraft to turn around its vertical axis, influenced by the vertical tail's moment arm, area, dynamic pressure, lift curve slope, sideslip angle, and sidewash angle, relative to the wing's reference area, span, and dynamic pressure. Yawing Moment Coefficient is denoted by C_n symbol.

How to calculate Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope using this online calculator? To use this online calculator for Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope, 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) & Wing Dynamic Pressure (Q_w) and hit the calculate button. Here is how the Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope calculation can be explained with given input values -> 1.401917 = 1.2*5*11*0.7*(0.05+0.067)/(5.08*1.15*0.66).

FAQ

What is Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope?

Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope is a measure of the rotational force that causes an aircraft to turn around its vertical axis, influenced by the vertical tail's moment arm, area, dynamic pressure, lift curve slope, sideslip angle, and sidewash angle, relative to the wing's reference area, span, and dynamic pressure and is represented as C_n = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(S*b*Q_w) or Yawing Moment Coefficient = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*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, 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 & Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.

How to calculate Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope?

How many ways are there to calculate Yawing Moment Coefficient?

In this formula, Yawing Moment Coefficient uses Vertical Tail Moment Arm, Vertical Tail Area, Vertical Tail Dynamic Pressure, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle, Reference Area, Wingspan & Wing Dynamic Pressure. We can use 2 other way(s) to calculate the same, which is/are as follows -

Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan)
Yawing Moment Coefficient = Vertical Tail Volume Ratio*Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)

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