Aerodynamic axial force Solution

STEP 0: Pre-Calculation Summary
Formula Used
Aerodynamic Axial Force = Axial force coefficient*Dynamic Pressure*Reference Area
X = Cx*q*S
This formula uses 4 Variables
Variables Used
Aerodynamic Axial Force - (Measured in Newton) - Aerodynamic axial force is the component of aerodynamic force along the roll axis of an aircraft.
Axial force coefficient - Axial force coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the roll 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
Axial force coefficient: 0.67 --> 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
X = Cx*q*S --> 0.67*10*5.08
Evaluating ... ...
X = 34.036
STEP 3: Convert Result to Output's Unit
34.036 Newton --> No Conversion Required
FINAL ANSWER
34.036 Newton <-- Aerodynamic Axial Force
(Calculation completed in 00.004 seconds)

Credits

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)
Yawing moment coefficient
Go Yawing Moment Coefficient = Yawing Moment/(Dynamic Pressure*Reference Area*Characteristic length)
Pitching moment
Go Pitching moment = Pitching moment coefficient*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

Aerodynamic axial force Formula

Aerodynamic Axial Force = Axial force coefficient*Dynamic Pressure*Reference Area
X = Cx*q*S

What are the two aerodynamic forces?

By convention, the single aerodynamic force is broken into two components: the drag force, which is opposed to the direction of motion, and the lift force, which acts perpendicular to the motion.

How to Calculate Aerodynamic axial force?

Aerodynamic axial force calculator uses Aerodynamic Axial Force = Axial force coefficient*Dynamic Pressure*Reference Area to calculate the Aerodynamic Axial Force, The Aerodynamic axial force is a product of the axial force coefficient, flight dynamic pressure and reference area. Aerodynamic Axial Force is denoted by X symbol.

How to calculate Aerodynamic axial force using this online calculator? To use this online calculator for Aerodynamic axial force, enter Axial force coefficient (Cx), Dynamic Pressure (q) & Reference Area (S) and hit the calculate button. Here is how the Aerodynamic axial force calculation can be explained with given input values -> 34.036 = 0.67*10*5.08.

FAQ

What is Aerodynamic axial force?
The Aerodynamic axial force is a product of the axial force coefficient, flight dynamic pressure and reference area and is represented as X = Cx*q*S or Aerodynamic Axial Force = Axial force coefficient*Dynamic Pressure*Reference Area. Axial force coefficient is the dimensionless coefficient associated with the component of aerodynamic forces along the roll 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 axial force?
The Aerodynamic axial force is a product of the axial force coefficient, flight dynamic pressure and reference area is calculated using Aerodynamic Axial Force = Axial force coefficient*Dynamic Pressure*Reference Area. To calculate Aerodynamic axial force, you need Axial force coefficient (Cx), Dynamic Pressure (q) & Reference Area (S). With our tool, you need to enter the respective value for Axial 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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