Rudder Control Effectiveness Calculator

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

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Static Stability and Control Formula PDF PDF Image

Rudder Control Effectiveness Solution

STEP 0: Pre-Calculation Summary

Formula Used

Yawing Moment Coefficient = Yawing Moment with Rudder Deflection Angle*Rudder Deflection Angle
C_n = C_nδr*δ_r
This formula uses 3 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.
Yawing Moment with Rudder Deflection Angle - Yawing moment with rudder deflection angle is the rate of change of deflection.
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

Yawing Moment with Rudder Deflection Angle: 0.96 --> 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 = C_nδr*δ_r --> 0.96*7.5

Evaluating ... ...

C_n = 7.2

STEP 3: Convert Result to Output's Unit

7.2 --> No Conversion Required

FINAL ANSWER

7.2 <-- Yawing Moment Coefficient

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Aerospace » Directional Control » Rudder Control Effectiveness

Credits

Created by Sastika Ilango

Sri Ramakrishna Engineering College (SREC), COIMBATORE

Sastika Ilango has created this Calculator and 9 more calculators!

Verified by Harsh Raj

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

Harsh Raj has verified this Calculator and 100+ more calculators!

< 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

Rudder Control Effectiveness Formula

LaTeX Go

Yawing Moment Coefficient = Yawing Moment with Rudder Deflection Angle*Rudder Deflection Angle
C_n = C_nδr*δ_r

What is rudder control effectiveness ?

The rudder control effectiveness is the rate of change of yawing moment with
rudder deflection angle

How to Calculate Rudder Control Effectiveness?

Rudder Control Effectiveness calculator uses Yawing Moment Coefficient = Yawing Moment with Rudder Deflection Angle*Rudder Deflection Angle to calculate the Yawing Moment Coefficient, Rudder Control Effectiveness is a measure of an aircraft's ability to respond to rudder input, which affects its directional control during flight, particularly during takeoff, landing, and low-speed flight regimes. Yawing Moment Coefficient is denoted by C_n symbol.

How to calculate Rudder Control Effectiveness using this online calculator? To use this online calculator for Rudder Control Effectiveness, enter Yawing Moment with Rudder Deflection Angle (C_nδr) & Rudder Deflection Angle (δ_r) and hit the calculate button. Here is how the Rudder Control Effectiveness calculation can be explained with given input values -> 52.5 = 0.96*7.5.

FAQ

What is Rudder Control Effectiveness?

Rudder Control Effectiveness is a measure of an aircraft's ability to respond to rudder input, which affects its directional control during flight, particularly during takeoff, landing, and low-speed flight regimes and is represented as C_n = C_nδr*δ_r or Yawing Moment Coefficient = Yawing Moment with Rudder Deflection Angle*Rudder Deflection Angle. Yawing moment with rudder deflection angle is the rate of change of deflection & Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw.

How to calculate Rudder Control Effectiveness?

Rudder Control Effectiveness is a measure of an aircraft's ability to respond to rudder input, which affects its directional control during flight, particularly during takeoff, landing, and low-speed flight regimes is calculated using Yawing Moment Coefficient = Yawing Moment with Rudder Deflection Angle*Rudder Deflection Angle. To calculate Rudder Control Effectiveness, you need Yawing Moment with Rudder Deflection Angle (C_nδr) & Rudder Deflection Angle (δ_r). With our tool, you need to enter the respective value for Yawing Moment with 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 Yawing Moment with 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 = -(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
Yawing Moment Coefficient = Negative Yawing Moment/Dynamic Pressure at Wing*Wing Reference Area*Wingspan

Home

FREE PDFs

🔍 Search