Rolling moment coefficient Calculator

✖Rolling Moment is the moment acting on the airplane about its roll axis.ⓘ Rolling Moment [𝑳]			+10% -10%
✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure [q]			+10% -10%
✖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.ⓘ Reference Area [S]			+10% -10%
✖Characteristic Length (used in aerodynamics) is a reference length characteristic of the object under consideration.ⓘ Characteristic Length [𝓁]			+10% -10%

✖Rolling Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its roll axis.ⓘ Rolling moment coefficient [C_𝒍]

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Rolling moment coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Rolling Moment Coefficient = Rolling Moment/(Dynamic Pressure*Reference Area*Characteristic Length)
C_𝒍 = 𝑳/(q*S*𝓁)
This formula uses 5 Variables

Variables Used

Rolling Moment Coefficient - Rolling Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its roll axis.
Rolling Moment - (Measured in Newton Meter) - Rolling Moment is the moment acting on the 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: 18.5928 Newton Meter --> 18.5928 Newton Meter 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

C_𝒍 = 𝑳/(q*S*𝓁) --> 18.5928/(10*5.08*0.6)

Evaluating ... ...

C_𝒍 = 0.61

STEP 3: Convert Result to Output's Unit

0.61 --> No Conversion Required

FINAL ANSWER

0.61 <-- Rolling Moment Coefficient

(Calculation completed in 00.008 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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PSG College of Technology (PSGCT), Coimbatore

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< Aircraft Dynamics Nomenclature Calculators

Aerodynamic Normal Force

LaTeX Go Aerodynamic Normal Force = Normal Force Coefficient*Dynamic Pressure*Reference Area

Aerodynamic Axial Force

LaTeX Go Aerodynamic Axial Force = Axial Force Coefficient*Dynamic Pressure*Reference Area

Side force coefficient

LaTeX Go Side Force Coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area)

Aerodynamic Side Force

LaTeX Go Aerodynamic Side Force = Side Force Coefficient*Dynamic Pressure*Reference Area

Rolling moment coefficient Formula

LaTeX Go

Rolling Moment Coefficient = Rolling Moment/(Dynamic Pressure*Reference Area*Characteristic Length)
C_𝒍 = 𝑳/(q*S*𝓁)

What is roll axis?

The roll axis (or longitudinal axis) has its origin at the center of gravity and is directed forward, parallel to the fuselage reference line.

How to Calculate Rolling moment coefficient?

Rolling moment coefficient calculator uses Rolling Moment Coefficient = Rolling Moment/(Dynamic Pressure*Reference Area*Characteristic Length) to calculate the Rolling Moment Coefficient, The Rolling moment coefficient is a measure of the rotational force that causes an object to rotate around a longitudinal axis, typically used to describe the aerodynamic characteristics of an airfoil or wing, it represents the relationship between the force of the rotating air and the physical properties of the wing, providing valuable insights for aircraft design and stability analysis. Rolling Moment Coefficient is denoted by C_𝒍 symbol.

How to calculate Rolling moment coefficient using this online calculator? To use this online calculator for Rolling moment coefficient, enter Rolling Moment (𝑳), Dynamic Pressure (q), Reference Area (S) & Characteristic Length (𝓁) and hit the calculate button. Here is how the Rolling moment coefficient calculation can be explained with given input values -> 0.606955 = 18.5928/(10*5.08*0.6).

FAQ

What is Rolling moment coefficient?

The Rolling moment coefficient is a measure of the rotational force that causes an object to rotate around a longitudinal axis, typically used to describe the aerodynamic characteristics of an airfoil or wing, it represents the relationship between the force of the rotating air and the physical properties of the wing, providing valuable insights for aircraft design and stability analysis and is represented as C_𝒍 = 𝑳/(q*S*𝓁) or Rolling Moment Coefficient = Rolling Moment/(Dynamic Pressure*Reference Area*Characteristic Length). Rolling Moment is the moment acting on the 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 coefficient?

The Rolling moment coefficient is a measure of the rotational force that causes an object to rotate around a longitudinal axis, typically used to describe the aerodynamic characteristics of an airfoil or wing, it represents the relationship between the force of the rotating air and the physical properties of the wing, providing valuable insights for aircraft design and stability analysis is calculated using Rolling Moment Coefficient = Rolling Moment/(Dynamic Pressure*Reference Area*Characteristic Length). To calculate Rolling moment coefficient, you need Rolling Moment (𝑳), Dynamic Pressure (q), Reference Area (S) & Characteristic Length (𝓁). With our tool, you need to enter the respective value for Rolling Moment, 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.

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