Yawing Moment with Rudder Deflection Angle Calculator

✖Vertical Tail Efficiency Factor is defined as the ratio of the yawing moment produced by the vertical tail to the product of its surface area and the square of the wingspan.ⓘ Vertical Tail Efficiency Factor [η_v]			+10% -10%
✖The velocity at tail plane of an aircraft refers to the airspeed experienced by the tail surfaces.ⓘ Velocity at Tail Plane [V_v]			+10% -10%
✖The Change in Coefficient of Lift of Tail Plane refers to the variation in lift generated by the tailplane of an aircraft.ⓘ Change in Coefficient of Lift of Tail Plane [d_CL,v]			+10% -10%
✖The change in rudder deflection angle refers to the variation in the angle by which the rudder is deflected from its initial position.ⓘ Change in Rudder Deflection Angle [d_δr]			+10% -10%

✖Yawing moment with rudder deflection angle is the rate of change of deflection.ⓘ Yawing Moment with Rudder Deflection Angle [C_nδr]

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Yawing Moment with Rudder Deflection Angle Solution

STEP 0: Pre-Calculation Summary

Formula Used

Yawing Moment with Rudder Deflection Angle = -(Vertical Tail Efficiency Factor*Velocity at Tail Plane)*(Change in Coefficient of Lift of Tail Plane/Change in Rudder Deflection Angle)
C_nδr = -(η_v*V_v)*(d_CL,v/d_δr)
This formula uses 5 Variables

Variables Used

Yawing Moment with Rudder Deflection Angle - Yawing moment with rudder deflection angle is the rate of change of deflection.
Vertical Tail Efficiency Factor - Vertical Tail Efficiency Factor is defined as the ratio of the yawing moment produced by the vertical tail to the product of its surface area and the square of the wingspan.
Velocity at Tail Plane - (Measured in Meter per Second) - The velocity at tail plane of an aircraft refers to the airspeed experienced by the tail surfaces.
Change in Coefficient of Lift of Tail Plane - The Change in Coefficient of Lift of Tail Plane refers to the variation in lift generated by the tailplane of an aircraft.
Change in Rudder Deflection Angle - The change in rudder deflection angle refers to the variation in the angle by which the rudder is deflected from its initial position.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Efficiency Factor: -1.1 --> No Conversion Required
Velocity at Tail Plane: 1.32 Meter per Second --> 1.32 Meter per Second No Conversion Required
Change in Coefficient of Lift of Tail Plane: 0.2 --> No Conversion Required
Change in Rudder Deflection Angle: 0.3 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_nδr = -(η_v*V_v)*(d_CL,v/d_δr) --> -((-1.1)*1.32)*(0.2/0.3)

Evaluating ... ...

C_nδr = 0.968

STEP 3: Convert Result to Output's Unit

0.968 --> No Conversion Required

FINAL ANSWER

0.968 <-- Yawing Moment with Rudder Deflection Angle

(Calculation completed in 00.006 seconds)

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Created by Sastika Ilango

Sri Ramakrishna Engineering College (SREC), COIMBATORE

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Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal

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< Directional Control Calculators

Yawing Moment Coefficient given Rudder Deflection

LaTeX Go Yawing Moment Coefficient = -(Dynamic Pressure at Vertical Tail/Dynamic Pressure at Wing)*((Distance between Rudder Hinge Line and Cg*Vertical Tail Area)/(Wingspan*Wing Reference Area))*(Coefficient of Lift/Deviated Rudder Deflection Angle)*Rudder Deflection Angle

Rudder Deflection Angle given Yawing Moment Coefficient

LaTeX Go Rudder Deflection Angle = -(Dynamic Pressure at Vertical Tail/Dynamic Pressure at Wing)*((Distance between Rudder Hinge Line and Cg*Vertical Tail Area)/(Wingspan*Wing Reference Area))*(Lift Coefficient/Deviated Rudder Deflection Angle)*Yawing Moment Coefficient

Yawing Moment given Rudder Deflection

LaTeX Go Yawing Moment Coefficient = Negative Yawing Moment/Dynamic Pressure at Wing*Wing Reference Area*Wingspan

Rudder Control Effectiveness

LaTeX Go Yawing Moment Coefficient = Yawing Moment with Rudder Deflection Angle*Rudder Deflection Angle

Yawing Moment with Rudder Deflection Angle Formula

LaTeX Go

What is yawing Moment with Rudder Deflection Angle ?

The yawing moment with rudder deflection angle refers to the rotational force exerted on an aircraft around its vertical axis due to the angle by which the rudder is deflected. When the rudder is deflected, it generates a side force, which in turn creates a yawing moment, causing the aircraft to yaw or turn about its vertical axis.

How to Calculate Yawing Moment with Rudder Deflection Angle?

Yawing Moment with Rudder Deflection Angle calculator uses Yawing Moment with Rudder Deflection Angle = -(Vertical Tail Efficiency Factor*Velocity at Tail Plane)*(Change in Coefficient of Lift of Tail Plane/Change in Rudder Deflection Angle) to calculate the Yawing Moment with Rudder Deflection Angle, Yawing Moment with Rudder Deflection Angle is a measure of the rotational force around the vertical axis of an aircraft, calculated by considering the vertical tail efficiency, velocity at the tail plane, and the change in coefficient of lift at the tail plane with respect to the rudder deflection angle, which is essential for understanding and controlling the aircraft's directional stability. Yawing Moment with Rudder Deflection Angle is denoted by C_nδr symbol.

How to calculate Yawing Moment with Rudder Deflection Angle using this online calculator? To use this online calculator for Yawing Moment with Rudder Deflection Angle, enter Vertical Tail Efficiency Factor (η_v), Velocity at Tail Plane (V_v), Change in Coefficient of Lift of Tail Plane (d_CL,v) & Change in Rudder Deflection Angle (d_δr) and hit the calculate button. Here is how the Yawing Moment with Rudder Deflection Angle calculation can be explained with given input values -> 0.968 = -((-1.1)*1.32)*(0.2/0.3).

FAQ

What is Yawing Moment with Rudder Deflection Angle?

Yawing Moment with Rudder Deflection Angle is a measure of the rotational force around the vertical axis of an aircraft, calculated by considering the vertical tail efficiency, velocity at the tail plane, and the change in coefficient of lift at the tail plane with respect to the rudder deflection angle, which is essential for understanding and controlling the aircraft's directional stability and is represented as C_nδr = -(η_v*V_v)*(d_CL,v/d_δr) or Yawing Moment with Rudder Deflection Angle = -(Vertical Tail Efficiency Factor*Velocity at Tail Plane)*(Change in Coefficient of Lift of Tail Plane/Change in Rudder Deflection Angle). Vertical Tail Efficiency Factor is defined as the ratio of the yawing moment produced by the vertical tail to the product of its surface area and the square of the wingspan, The velocity at tail plane of an aircraft refers to the airspeed experienced by the tail surfaces, The Change in Coefficient of Lift of Tail Plane refers to the variation in lift generated by the tailplane of an aircraft & The change in rudder deflection angle refers to the variation in the angle by which the rudder is deflected from its initial position.

How to calculate Yawing Moment with Rudder Deflection Angle?

Yawing Moment with Rudder Deflection Angle is a measure of the rotational force around the vertical axis of an aircraft, calculated by considering the vertical tail efficiency, velocity at the tail plane, and the change in coefficient of lift at the tail plane with respect to the rudder deflection angle, which is essential for understanding and controlling the aircraft's directional stability is calculated using Yawing Moment with Rudder Deflection Angle = -(Vertical Tail Efficiency Factor*Velocity at Tail Plane)*(Change in Coefficient of Lift of Tail Plane/Change in Rudder Deflection Angle). To calculate Yawing Moment with Rudder Deflection Angle, you need Vertical Tail Efficiency Factor (η_v), Velocity at Tail Plane (V_v), Change in Coefficient of Lift of Tail Plane (d_CL,v) & Change in Rudder Deflection Angle (d_δr). With our tool, you need to enter the respective value for Vertical Tail Efficiency Factor, Velocity at Tail Plane, Change in Coefficient of Lift of Tail Plane & Change in Rudder Deflection Angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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