Aerodynamic Normal Force Calculator

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

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

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Aerodynamic Normal Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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

Normal Force Coefficient: 0.38 --> 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

Z = C_z*q*S --> 0.38*10*5.08

Evaluating ... ...

Z = 19.304

STEP 3: Convert Result to Output's Unit

19.304 Newton --> No Conversion Required

FINAL ANSWER

19.304 Newton <-- Aerodynamic Normal Force

(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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Verified by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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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

Aerodynamic Normal Force Formula

LaTeX Go

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

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How to Calculate Aerodynamic Normal Force?

Aerodynamic Normal Force calculator uses Aerodynamic Normal Force = Normal Force Coefficient*Dynamic Pressure*Reference Area to calculate the Aerodynamic Normal Force, Aerodynamic Normal Force is a measure of the force exerted by the air pressure on an object, perpendicular to the surface of the object, resulting from the air's resistance to the object's motion, it is a crucial concept in aerodynamics, essential for understanding and predicting the behavior of aircraft, wind turbines, and other systems interacting with air. Aerodynamic Normal Force is denoted by Z symbol.

How to calculate Aerodynamic Normal Force using this online calculator? To use this online calculator for Aerodynamic Normal Force, enter Normal Force Coefficient (C_z), Dynamic Pressure (q) & Reference Area (S) and hit the calculate button. Here is how the Aerodynamic Normal Force calculation can be explained with given input values -> 19.304 = 0.38*10*5.08.

FAQ

What is Aerodynamic Normal Force?

Aerodynamic Normal Force is a measure of the force exerted by the air pressure on an object, perpendicular to the surface of the object, resulting from the air's resistance to the object's motion, it is a crucial concept in aerodynamics, essential for understanding and predicting the behavior of aircraft, wind turbines, and other systems interacting with air and is represented as Z = C_z*q*S or Aerodynamic Normal Force = Normal Force Coefficient*Dynamic Pressure*Reference Area. Normal Force Coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the yaw axis on 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 Aerodynamic Normal Force?

Aerodynamic Normal Force is a measure of the force exerted by the air pressure on an object, perpendicular to the surface of the object, resulting from the air's resistance to the object's motion, it is a crucial concept in aerodynamics, essential for understanding and predicting the behavior of aircraft, wind turbines, and other systems interacting with air is calculated using Aerodynamic Normal Force = Normal Force Coefficient*Dynamic Pressure*Reference Area. To calculate Aerodynamic Normal Force, you need Normal Force Coefficient (C_z), Dynamic Pressure (q) & Reference Area (S). With our tool, you need to enter the respective value for Normal Force Coefficient, 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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