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)
Cz = 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
Cz = Z/(q*S) --> 19/(10*5.08)
Evaluating ... ...
Cz = 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 00.004 seconds)

Credits

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

Normal Force Coefficient with Aerodynamic Normal Force Formula

​LaTeX ​Go
Normal Force Coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area)
Cz = 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 Cz 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 Cz = 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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