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Normal Force Coefficient with Aerodynamic Normal Force Formula

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Normal Force Coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the yaw axis on an aircraft. Check FAQs

C z = \frac{Z}{q \cdot S}

C_z - Normal Force Coefficient?Z - Aerodynamic Normal Force?q - Dynamic Pressure?S - Reference Area?

Normal Force Coefficient with Aerodynamic Normal Force Example

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Here is how the Normal Force Coefficient with Aerodynamic Normal Force equation looks like with Values.

Here is how the Normal Force Coefficient with Aerodynamic Normal Force equation looks like with Units.

Here is how the Normal Force Coefficient with Aerodynamic Normal Force equation looks like.

0.374 = \frac{19}{10 \cdot 5.08}

0.374 = \frac{19N}{10Pa \cdot 5.08m²}

0.374 = \frac{19}{10 \cdot 5.08}

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Normal Force Coefficient with Aerodynamic Normal Force Solution

Follow our step by step solution on how to calculate Normal Force Coefficient with Aerodynamic Normal Force?

FIRST Step Consider the formula

C z = \frac{Z}{q \cdot S}

Next Step Substitute values of Variables

∴

C z = \frac{19N}{10Pa \cdot 5.08m²}

Next Step Prepare to Evaluate

∴

C z = \frac{19}{10 \cdot 5.08}

Next Step Evaluate

∴

C z = 0.374015748031496

LAST Step Rounding Answer

∴

C z = 0.374

Normal Force Coefficient with Aerodynamic Normal Force Formula Elements

Variables

Normal Force Coefficient

Normal Force Coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the yaw axis on an aircraft.

Symbol: C_z

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Normal Force Coefficient

Aerodynamic Normal Force

Aerodynamic Normal Force is the component of aerodynamic force along the yaw axis of an aircraft.

Symbol: Z

Measurement: ForceUnit: N

Note: Value can be positive or negative.

Formulas to find Aerodynamic Normal Force

Dynamic Pressure

Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.

Symbol: q

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Dynamic Pressure

Reference Area

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.

Symbol: S

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Reference Area

Other formulas in Aircraft Dynamics Nomenclature category

Go Aerodynamic Axial Force

X = C x \cdot q \cdot S

Go Aerodynamic Side Force

Y = C y \cdot q \cdot S

Go Aerodynamic Normal Force

Z = C z \cdot q \cdot S

Go Side force coefficient

C y = \frac{Y}{q \cdot S}

How to Evaluate Normal Force Coefficient with Aerodynamic Normal Force?

Normal Force Coefficient with Aerodynamic Normal Force evaluator uses Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area) to evaluate the Normal Force Coefficient, The Normal Force Coefficient with Aerodynamic Normal Force is a dimensionless quantity that characterizes the normal force exerted on an object in a fluid flow, providing a measure of the aerodynamic force perpendicular to the surface of the object, it is a fundamental parameter in aerodynamics and wind engineering, used to predict the behavior of objects in air or water flows. Normal Force Coefficient is denoted by C_z symbol.

How to evaluate Normal Force Coefficient with Aerodynamic Normal Force using this online evaluator? To use this online evaluator for Normal Force Coefficient with Aerodynamic Normal Force, enter Aerodynamic Normal Force (Z), Dynamic Pressure (q) & Reference Area (S) and hit the calculate button.

FAQs on Normal Force Coefficient with Aerodynamic Normal Force

What is the formula to find Normal Force Coefficient with Aerodynamic Normal Force?

The formula of Normal Force Coefficient with Aerodynamic Normal Force is expressed as Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area). Here is an example- 0.374016 = 19/(10*5.08).

How to calculate Normal Force Coefficient with Aerodynamic Normal Force?

With Aerodynamic Normal Force (Z), Dynamic Pressure (q) & Reference Area (S) we can find Normal Force Coefficient with Aerodynamic Normal Force using the formula - Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area).

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Normal Force Coefficient with Aerodynamic Normal Force Formula

Normal Force Coefficient with Aerodynamic Normal Force Example

Normal Force Coefficient with Aerodynamic Normal Force Solution

Normal Force Coefficient with Aerodynamic Normal Force Formula Elements

Other formulas in Aircraft Dynamics Nomenclature category

How to Evaluate Normal Force Coefficient with Aerodynamic Normal Force?

FAQs on Normal Force Coefficient with Aerodynamic Normal Force

Variable Name