Rolling moment Solution

STEP 0: Pre-Calculation Summary
Formula Used
Rolling moment = Rolling moment coefficient*Dynamic Pressure*Reference Area*Characteristic length
𝑳 = C𝒍*q*S*𝓁
This formula uses 5 Variables
Variables Used
Rolling moment - (Measured in Newton Meter) - Rolling moment is the moment acting on the airplane about its roll axis.
Rolling moment coefficient - Rolling moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its roll axis.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
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.
Characteristic length - (Measured in Meter) - Characteristic length (used in aerodynamics) is a reference length characteristic of the object under consideration.
STEP 1: Convert Input(s) to Base Unit
Rolling moment coefficient: 0.61 --> No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Characteristic length: 0.6 Meter --> 0.6 Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
𝑳 = C𝒍*q*S*𝓁 --> 0.61*10*5.08*0.6
Evaluating ... ...
𝑳 = 18.5928
STEP 3: Convert Result to Output's Unit
18.5928 Newton Meter --> No Conversion Required
FINAL ANSWER
18.5928 Newton Meter <-- Rolling moment
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Verified by Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 300+ more calculators!

18 Aircraft Dynamics Nomenclature Calculators

Sideslip angle
Go Sideslip Angle = asin(Velocity along pitch axis/(sqrt((Velocity along Roll Axis^2)+(Velocity along pitch axis^2)+(Velocity along yaw axis^2))))
Mean Aerodynamic Chord for Propeller-Driven Airplane
Go Mean aerodynamic chord = (1/Reference Area)*int(Chord Length^2,x,-Wingspan/2,Wingspan/2)
Pitching moment coefficient
Go Pitching moment coefficient = Pitching moment/(Dynamic Pressure*Reference Area*Characteristic length)
Rolling moment coefficient
Go Rolling moment coefficient = Rolling moment/(Dynamic Pressure*Reference Area*Characteristic length)
Yawing moment coefficient
Go Yawing Moment Coefficient = Yawing Moment/(Dynamic Pressure*Reference Area*Characteristic length)
Pitching moment
Go Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length
Rolling moment
Go Rolling moment = Rolling moment coefficient*Dynamic Pressure*Reference Area*Characteristic length
Yawing moment
Go Yawing Moment = Yawing Moment Coefficient*Dynamic Pressure*Reference Area*Characteristic length
Normal force coefficient with aerodynamic normal force
Go Normal force coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area)
Aerodynamic normal force
Go Aerodynamic Normal Force = Normal force coefficient*Dynamic Pressure*Reference Area
Aerodynamic axial force
Go Aerodynamic Axial Force = Axial force coefficient*Dynamic Pressure*Reference Area
Side force coefficient
Go Side force coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area)
Aerodynamic side force
Go Aerodynamic Side Force = Side force coefficient*Dynamic Pressure*Reference Area
Angle of attack
Go Angle of Attack = atan(Velocity along yaw axis/Velocity along Roll Axis)
Velocity along pitch axis for small sideslip angle
Go Velocity along pitch axis = Sideslip Angle*Velocity along Roll Axis
Velocity along roll axis for small sideslip angle
Go Velocity along Roll Axis = Velocity along pitch axis/Sideslip Angle
Velocity along roll axis for small angle of attack
Go Velocity along Roll Axis = Velocity along yaw axis/Angle of Attack
Velocity along yaw axis for small angle of attack
Go Velocity along yaw axis = Velocity along Roll Axis*Angle of Attack

Rolling moment Formula

Rolling moment = Rolling moment coefficient*Dynamic Pressure*Reference Area*Characteristic length
𝑳 = C𝒍*q*S*𝓁

What is the characteristic length for calculating rolling moment?

Characteristic length is taken as the wing span for the rolling moment of an aircraft. The wingspan of an aircraft is always measured in a straight line, from wingtip to wingtip, independently of wing shape or sweep.

How to Calculate Rolling moment?

Rolling moment calculator uses Rolling moment = Rolling moment coefficient*Dynamic Pressure*Reference Area*Characteristic length to calculate the Rolling moment, The Rolling moment for an aircraft is a function of the rolling moment coefficient, dynamic pressure, reference area, and characteristic length. Rolling moment is denoted by 𝑳 symbol.

How to calculate Rolling moment using this online calculator? To use this online calculator for Rolling moment, enter Rolling moment coefficient (C𝒍), Dynamic Pressure (q), Reference Area (S) & Characteristic length (𝓁) and hit the calculate button. Here is how the Rolling moment calculation can be explained with given input values -> 18.5928 = 0.61*10*5.08*0.6.

FAQ

What is Rolling moment?
The Rolling moment for an aircraft is a function of the rolling moment coefficient, dynamic pressure, reference area, and characteristic length and is represented as 𝑳 = C𝒍*q*S*𝓁 or Rolling moment = Rolling moment coefficient*Dynamic Pressure*Reference Area*Characteristic length. Rolling moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its roll axis, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, 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 & Characteristic length (used in aerodynamics) is a reference length characteristic of the object under consideration.
How to calculate Rolling moment?
The Rolling moment for an aircraft is a function of the rolling moment coefficient, dynamic pressure, reference area, and characteristic length is calculated using Rolling moment = Rolling moment coefficient*Dynamic Pressure*Reference Area*Characteristic length. To calculate Rolling moment, you need Rolling moment coefficient (C𝒍), Dynamic Pressure (q), Reference Area (S) & Characteristic length (𝓁). With our tool, you need to enter the respective value for Rolling moment coefficient, Dynamic Pressure, Reference Area & Characteristic length and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!