Yawing Moment Coefficient for given Vertical Tail Volume Ratio Calculator

✖Vertical Tail Volume Ratio relates to the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's e.g., the wing area, and the wingspan.ⓘ Vertical Tail Volume Ratio [V_v]			+10% -10%
✖Vertical Tail Efficiency is the tail efficiency associated with the vertical tail of an aircraft.ⓘ Vertical Tail Efficiency [η_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 for given Vertical Tail Volume Ratio [C_n]

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Yawing Moment Coefficient for given Vertical Tail Volume Ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Yawing Moment Coefficient = Vertical Tail Volume Ratio*Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)
C_n = V_v*η_v*C_v*(β+σ)
This formula uses 6 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 Volume Ratio - Vertical Tail Volume Ratio relates to the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's e.g., the wing area, and the wingspan.
Vertical Tail Efficiency - Vertical Tail Efficiency is the tail efficiency 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.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Volume Ratio: 1.02 --> No Conversion Required
Vertical Tail Efficiency: 16.66 --> 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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_n = V_v*η_v*C_v*(β+σ) --> 1.02*16.66*0.7*(0.05+0.067)

Evaluating ... ...

C_n = 1.39174308

STEP 3: Convert Result to Output's Unit

1.39174308 --> No Conversion Required

FINAL ANSWER

1.39174308 ≈ 1.391743 <-- 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 Volume Ratio Formula

LaTeX Go

Yawing Moment Coefficient = Vertical Tail Volume Ratio*Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)
C_n = V_v*η_v*C_v*(β+σ)

What is a flying wing?

A flying wing is a tailless design that lacks a distinct fuselage, having the pilot, engines, etc., located directly in or on the wing.

How to Calculate Yawing Moment Coefficient for given Vertical Tail Volume Ratio?

Yawing Moment Coefficient for given Vertical Tail Volume Ratio calculator uses Yawing Moment Coefficient = Vertical Tail Volume Ratio*Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle) to calculate the Yawing Moment Coefficient, Yawing moment coefficient for given vertical tail volume ratio is a measure of the rotational force around the vertical axis, influenced by the vertical tail's volume, efficiency, and lift characteristics, as well as the angles of sideslip and sidewash. Yawing Moment Coefficient is denoted by C_n symbol.

How to calculate Yawing Moment Coefficient for given Vertical Tail Volume Ratio using this online calculator? To use this online calculator for Yawing Moment Coefficient for given Vertical Tail Volume Ratio, enter Vertical Tail Volume Ratio (V_v), Vertical Tail Efficiency (η_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β) & Sidewash Angle (σ) and hit the calculate button. Here is how the Yawing Moment Coefficient for given Vertical Tail Volume Ratio calculation can be explained with given input values -> 1.391743 = 1.02*16.66*0.7*(0.05+0.067).

FAQ

What is Yawing Moment Coefficient for given Vertical Tail Volume Ratio?

Yawing moment coefficient for given vertical tail volume ratio is a measure of the rotational force around the vertical axis, influenced by the vertical tail's volume, efficiency, and lift characteristics, as well as the angles of sideslip and sidewash and is represented as C_n = V_v*η_v*C_v*(β+σ) or Yawing Moment Coefficient = Vertical Tail Volume Ratio*Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle). Vertical Tail Volume Ratio relates to the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's e.g., the wing area, and the wingspan, Vertical Tail Efficiency is the tail efficiency 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.

How to calculate Yawing Moment Coefficient for given Vertical Tail Volume Ratio?

Yawing moment coefficient for given vertical tail volume ratio is a measure of the rotational force around the vertical axis, influenced by the vertical tail's volume, efficiency, and lift characteristics, as well as the angles of sideslip and sidewash is calculated using Yawing Moment Coefficient = Vertical Tail Volume Ratio*Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle). To calculate Yawing Moment Coefficient for given Vertical Tail Volume Ratio, you need Vertical Tail Volume Ratio (V_v), Vertical Tail Efficiency (η_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β) & Sidewash Angle (σ). With our tool, you need to enter the respective value for Vertical Tail Volume Ratio, Vertical Tail Efficiency, Vertical Tail Lift Curve Slope, Sideslip Angle & Sidewash Angle 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 Yawing Moment Coefficient?

In this formula, Yawing Moment Coefficient uses Vertical Tail Volume Ratio, Vertical Tail Efficiency, Vertical Tail Lift Curve Slope, Sideslip Angle & Sidewash Angle. 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 Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Wing Dynamic Pressure)

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