Normal Force Coefficient with Aerodynamic Normal Force Calculator

✖Aerodynamic Normal Force is the component of aerodynamic force along the yaw axis of an aircraft.ⓘ Aerodynamic Normal Force [Z]			+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%

✖Normal Force Coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the yaw axis on an aircraft.ⓘ Normal Force Coefficient with Aerodynamic Normal Force [C_z]

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Normal Force Coefficient with Aerodynamic Normal Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area)
C_z = Z/(q*S)
This formula uses 4 Variables

Variables Used

Normal Force Coefficient - Normal Force Coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the yaw axis on an aircraft.
Aerodynamic Normal Force - (Measured in Newton) - Aerodynamic Normal Force is the component of aerodynamic force along the yaw 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 Normal Force: 19 Newton --> 19 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_z = Z/(q*S) --> 19/(10*5.08)

Evaluating ... ...

C_z = 0.374015748031496

STEP 3: Convert Result to Output's Unit

0.374015748031496 --> No Conversion Required

FINAL ANSWER

0.374015748031496 ≈ 0.374016 <-- Normal Force Coefficient

(Calculation completed in 00.020 seconds)

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

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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

Normal Force Coefficient with Aerodynamic Normal Force Formula

LaTeX Go

Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area)
C_z = Z/(q*S)

What is the purpose of aerodynamic coefficients?

Aerodynamic Coefficients are non-dimensional numbers that are used to determine the aerodynamic characteristics of an aircraft.

How to Calculate Normal Force Coefficient with Aerodynamic Normal Force?

Normal Force Coefficient with Aerodynamic Normal Force calculator uses Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area) to calculate 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 calculate Normal Force Coefficient with Aerodynamic Normal Force using this online calculator? To use this online calculator for Normal Force Coefficient with Aerodynamic Normal Force, enter Aerodynamic Normal Force (Z), Dynamic Pressure (q) & Reference Area (S) and hit the calculate button. Here is how the Normal Force Coefficient with Aerodynamic Normal Force calculation can be explained with given input values -> 0.374016 = 19/(10*5.08).

FAQ

What is Normal Force Coefficient with Aerodynamic Normal Force?

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 and is represented as C_z = Z/(q*S) or Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area). Aerodynamic Normal Force is the component of aerodynamic force along the yaw 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 Normal Force Coefficient with Aerodynamic Normal Force?

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 is calculated using Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area). To calculate Normal Force Coefficient with Aerodynamic Normal Force, you need Aerodynamic Normal Force (Z), Dynamic Pressure (q) & Reference Area (S). With our tool, you need to enter the respective value for Aerodynamic Normal 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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