Yawing Moment Coefficient given Rudder Deflection Calculator

✖The Dynamic Pressure at Vertical Tail of an aircraft is the pressure exerted by the air flowing past the tail due to the aircraft's forward motion.ⓘ Dynamic Pressure at Vertical Tail [Q_v]			+10% -10%
✖Dynamic Pressure at Wing Represents the kinetic energy per unit volume of air due to its motion.ⓘ Dynamic Pressure at Wing [Q_w]			+10% -10%
✖Distance between Rudder Hinge Line and Cg is the geometric property which define the moment arm of the rudder force, affecting the overall yawing moment produced.ⓘ Distance between Rudder Hinge Line and Cg [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%
✖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 Reference Area is the planform area, refers to the projected area of the wing, as if viewed directly from above.ⓘ Wing Reference Area [s]			+10% -10%
✖Coefficient of lift is a dimensionless quantity that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity, and an associated reference area.ⓘ Coefficient of Lift [d_cl]			+10% -10%
✖Deviated Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw.ⓘ Deviated Rudder Deflection Angle [dδ_r]			+10% -10%
✖Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw.ⓘ Rudder Deflection Angle [δ_r]			+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 given Rudder Deflection [C_n]

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Yawing Moment Coefficient given Rudder Deflection Solution

STEP 0: Pre-Calculation Summary

Formula Used

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
C_n = -(Q_v/Q_w)*((l_v*S_v)/(b*s))*(d_cl/dδ_r)*δ_r
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.
Dynamic Pressure at Vertical Tail - (Measured in Pascal) - The Dynamic Pressure at Vertical Tail of an aircraft is the pressure exerted by the air flowing past the tail due to the aircraft's forward motion.
Dynamic Pressure at Wing - (Measured in Pascal) - Dynamic Pressure at Wing Represents the kinetic energy per unit volume of air due to its motion.
Distance between Rudder Hinge Line and Cg - (Measured in Meter) - Distance between Rudder Hinge Line and Cg is the geometric property which define the moment arm of the rudder force, affecting the overall yawing moment produced.
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.
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 Reference Area - (Measured in Square Meter) - Wing Reference Area is the planform area, refers to the projected area of the wing, as if viewed directly from above.
Coefficient of Lift - Coefficient of lift is a dimensionless quantity that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity, and an associated reference area.
Deviated Rudder Deflection Angle - (Measured in Radian) - Deviated Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw.
Rudder Deflection Angle - (Measured in Radian) - Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw.

STEP 1: Convert Input(s) to Base Unit

Dynamic Pressure at Vertical Tail: 60 Pascal --> 60 Pascal No Conversion Required
Dynamic Pressure at Wing: 90 Pascal --> 90 Pascal No Conversion Required
Distance between Rudder Hinge Line and Cg: 5.5 Meter --> 5.5 Meter No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required
Wingspan: 6.7 Meter --> 6.7 Meter No Conversion Required
Wing Reference Area: 8.5 Square Meter --> 8.5 Square Meter No Conversion Required
Coefficient of Lift: -3.9 --> No Conversion Required
Deviated Rudder Deflection Angle: 1.3 Radian --> 1.3 Radian No Conversion Required
Rudder Deflection Angle: 7.5 Radian --> 7.5 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_n = -(Q_v/Q_w)*((l_v*S_v)/(b*s))*(d_cl/dδ_r)*δ_r --> -(60/90)*((5.5*5)/(6.7*8.5))*((-3.9)/1.3)*7.5

Evaluating ... ...

C_n = 7.243195785777

STEP 3: Convert Result to Output's Unit

7.243195785777 --> No Conversion Required

FINAL ANSWER

7.243195785777 ≈ 7.243196 <-- Yawing Moment Coefficient

(Calculation completed in 00.036 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Aerospace » Directional Control » Yawing Moment Coefficient given Rudder Deflection

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Sri Ramakrishna Engineering College (SREC), COIMBATORE

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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 Coefficient given Rudder Deflection Formula

LaTeX Go

what is Yawing Moment Coefficient given Rudder Deflection?

The Yawing Moment Coefficient given Rudder Deflection formula is defined as the generation of a yaw moment, which is a rotational force around the aircraft's vertical axis. This moment causes the aircraft to yaw (turn its nose) left or right. The pilot controls the yaw moment by deflecting the rudder, a hinged surface on the vertical stabilizer.

How to Calculate Yawing Moment Coefficient given Rudder Deflection?

Yawing Moment Coefficient given Rudder Deflection calculator uses 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 to calculate the Yawing Moment Coefficient, Yawing Moment Coefficient given Rudder Deflection is a measure of the rotational force around the vertical axis of an aircraft, caused by the deflection of the rudder, and is influenced by the dynamic pressure at the vertical tail, the distance between the rudder hinge line and center of gravity, and the wing reference area, this coefficient is a critical parameter in aircraft design, as it affects the stability and control of the aircraft during flight. Yawing Moment Coefficient is denoted by C_n symbol.

How to calculate Yawing Moment Coefficient given Rudder Deflection using this online calculator? To use this online calculator for Yawing Moment Coefficient given Rudder Deflection, enter Dynamic Pressure at Vertical Tail (Q_v), Dynamic Pressure at Wing (Q_w), Distance between Rudder Hinge Line and Cg (l_v), Vertical Tail Area (S_v), Wingspan (b), Wing Reference Area (s), Coefficient of Lift (d_cl), Deviated Rudder Deflection Angle (dδ_r) & Rudder Deflection Angle (δ_r) and hit the calculate button. Here is how the Yawing Moment Coefficient given Rudder Deflection calculation can be explained with given input values -> 7.614642 = -(60/90)*((5.5*5)/(6.7*8.5))*((-3.9)/1.3)*7.5.

FAQ

What is Yawing Moment Coefficient given Rudder Deflection?

Yawing Moment Coefficient given Rudder Deflection is a measure of the rotational force around the vertical axis of an aircraft, caused by the deflection of the rudder, and is influenced by the dynamic pressure at the vertical tail, the distance between the rudder hinge line and center of gravity, and the wing reference area, this coefficient is a critical parameter in aircraft design, as it affects the stability and control of the aircraft during flight and is represented as C_n = -(Q_v/Q_w)*((l_v*S_v)/(b*s))*(d_cl/dδ_r)*δ_r or 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. The Dynamic Pressure at Vertical Tail of an aircraft is the pressure exerted by the air flowing past the tail due to the aircraft's forward motion, Dynamic Pressure at Wing Represents the kinetic energy per unit volume of air due to its motion, Distance between Rudder Hinge Line and Cg is the geometric property which define the moment arm of the rudder force, affecting the overall yawing moment produced, The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip, Wing Reference Area is the planform area, refers to the projected area of the wing, as if viewed directly from above, Coefficient of lift is a dimensionless quantity that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity, and an associated reference area, Deviated Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw & Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw.

How to calculate Yawing Moment Coefficient given Rudder Deflection?

Yawing Moment Coefficient given Rudder Deflection is a measure of the rotational force around the vertical axis of an aircraft, caused by the deflection of the rudder, and is influenced by the dynamic pressure at the vertical tail, the distance between the rudder hinge line and center of gravity, and the wing reference area, this coefficient is a critical parameter in aircraft design, as it affects the stability and control of the aircraft during flight is calculated using 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. To calculate Yawing Moment Coefficient given Rudder Deflection, you need Dynamic Pressure at Vertical Tail (Q_v), Dynamic Pressure at Wing (Q_w), Distance between Rudder Hinge Line and Cg (l_v), Vertical Tail Area (S_v), Wingspan (b), Wing Reference Area (s), Coefficient of Lift (d_cl), Deviated Rudder Deflection Angle (dδ_r) & Rudder Deflection Angle (δ_r). With our tool, you need to enter the respective value for 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 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 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. We can use 2 other way(s) to calculate the same, which is/are as follows -

Yawing Moment Coefficient = Negative Yawing Moment/Dynamic Pressure at Wing*Wing Reference Area*Wingspan
Yawing Moment Coefficient = Yawing Moment with Rudder Deflection Angle*Rudder Deflection Angle

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