Side force coefficient Calculator

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Introduction and Governing Equations

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Preliminary Aerodynamics

✖Aerodynamic side force is the component of aerodynamic force along the pitch axis of an aircraft.ⓘ Aerodynamic Side Force [Y]			+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%

✖Side force coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the pitch axis on an aircraft.ⓘ Side force coefficient [C_y]

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Formula

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Side force coefficient

Formula

`"C"_{"y"} = "Y"/("q"*"S")`

Example

`"0.748031"="38N"/("10Pa"*"5.08m²")`

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Side force coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Side force coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area)
C_y = Y/(q*S)
This formula uses 4 Variables

Variables Used

Side force coefficient - Side force coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the pitch axis on an aircraft.
Aerodynamic Side Force - (Measured in Newton) - Aerodynamic side force is the component of aerodynamic force along the pitch axis of an aircraft.
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.

STEP 1: Convert Input(s) to Base Unit

Aerodynamic Side Force: 38 Newton --> 38 Newton 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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_y = Y/(q*S) --> 38/(10*5.08)

Evaluating ... ...

C_y = 0.748031496062992

STEP 3: Convert Result to Output's Unit

0.748031496062992 --> No Conversion Required

FINAL ANSWER

0.748031496062992 ≈ 0.748031 <-- Side force coefficient

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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Indian Institute of Technology (IIT), Bombay

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< 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)

Pitching moment

Go Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length

Yawing moment coefficient

Go Yawing Moment Coefficient = Yawing Moment/(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

Side force coefficient Formula

Side force coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area)
C_y = Y/(q*S)

Why is lift coefficient important?

The value of the maximum lift coefficient is a very important airfoil characteristic because it determines the minimum speed at which an airplane can fly.

How to Calculate Side force coefficient?

Side force coefficient calculator uses Side force coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area) to calculate the Side force coefficient, The Side force coefficient is dependent on the aerodynamic side force, dynamic pressure, and reference area. Side force coefficient is denoted by C_y symbol.

How to calculate Side force coefficient using this online calculator? To use this online calculator for Side force coefficient, enter Aerodynamic Side Force (Y), Dynamic Pressure (q) & Reference Area (S) and hit the calculate button. Here is how the Side force coefficient calculation can be explained with given input values -> 0.748031 = 38/(10*5.08).

FAQ

What is Side force coefficient?

The Side force coefficient is dependent on the aerodynamic side force, dynamic pressure, and reference area and is represented as C_y = Y/(q*S) or Side force coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area). Aerodynamic side force is the component of aerodynamic force along the pitch axis of an aircraft, 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.

How to calculate Side force coefficient?

The Side force coefficient is dependent on the aerodynamic side force, dynamic pressure, and reference area is calculated using Side force coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area). To calculate Side force coefficient, you need Aerodynamic Side Force (Y), Dynamic Pressure (q) & Reference Area (S). With our tool, you need to enter the respective value for Aerodynamic Side Force, Dynamic Pressure & Reference Area 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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