Yawing Moment Coefficient using Wingspan Solution

STEP 0: Pre-Calculation Summary
Formula Used
Yawing moment coefficient = Moment produced by vertical tail/(Wing dynamic pressure*Reference Area*Wingspan)
Cn = Nv/(Qw*S*b)
This formula uses 5 Variables
Variables Used
Yawing moment coefficient - Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.
Moment produced by vertical tail - (Measured in Newton Meter) - The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.
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.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
STEP 1: Convert Input(s) to Base Unit
Moment produced by vertical tail: 2 Newton Meter --> 2 Newton Meter No Conversion Required
Wing dynamic pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 50 Meter --> 50 Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Cn = Nv/(Qw*S*b) --> 2/(0.66*5.08*50)
Evaluating ... ...
Cn = 0.0119303268909568
STEP 3: Convert Result to Output's Unit
0.0119303268909568 --> No Conversion Required
FINAL ANSWER
0.0119303268909568 0.01193 <-- Yawing moment coefficient
(Calculation completed in 00.020 seconds)

Credits

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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10+ Aerodynamic Parameters Calculators

Yawing moment coefficient for given vertical tail lift curve slope
Go Yawing moment coefficient = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Wing dynamic pressure)
Sidewash Angle given Yawing Moment Coefficient using Wingspan
Go Sidewash angle = (Yawing moment coefficient*Reference Area*Wingspan*Wing dynamic pressure/(Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope))-Sideslip angle
Sideslip angle for given moment produced by vertical tail
Go Sideslip angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sidewash angle
Sidewash angle for given moment produced by vertical tail
Go Sidewash angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sideslip angle
Sidewash angle for given yawing moment coefficient
Go Sidewash angle = (Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sideslip angle
Sideslip angle for yawing moment coefficient given vertical tail volume ratio
Go Sideslip angle = (Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sidewash angle
Yawing moment coefficient for given vertical tail volume ratio
Go Yawing moment coefficient = Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)
Yawing Moment Coefficient using Wingspan
Go Yawing moment coefficient = Moment produced by vertical tail/(Wing dynamic pressure*Reference Area*Wingspan)
Sideslip angle for Aircraft
Go Sideslip angle = Vertical tail angle of attack-Sidewash angle
Sidewash angle
Go Sidewash angle = Vertical tail angle of attack-Sideslip angle

Yawing Moment Coefficient using Wingspan Formula

Yawing moment coefficient = Moment produced by vertical tail/(Wing dynamic pressure*Reference Area*Wingspan)
Cn = Nv/(Qw*S*b)

Why is yaw important?

Rudder turns or yawing at low speed can result in one wing stalling before the other one, causing the potential of a spin. Additionally, yawing causes one wing to produce more lift than the opposite wing, causing a roll. Controlling the roll without the yaw is a better way to turn the airplane.

How to Calculate Yawing Moment Coefficient using Wingspan?

Yawing Moment Coefficient using Wingspan calculator uses Yawing moment coefficient = Moment produced by vertical tail/(Wing dynamic pressure*Reference Area*Wingspan) to calculate the Yawing moment coefficient, The Yawing moment coefficient using wingspan is a moment that lends to rotate an airplane about its vertical axis yawing moment is positive when it tends to turn the plane to the right and negative when it turns the plane to the left. Yawing moment coefficient is denoted by Cn symbol.

How to calculate Yawing Moment Coefficient using Wingspan using this online calculator? To use this online calculator for Yawing Moment Coefficient using Wingspan, enter Moment produced by vertical tail (Nv), Wing dynamic pressure (Qw), Reference Area (S) & Wingspan (b) and hit the calculate button. Here is how the Yawing Moment Coefficient using Wingspan calculation can be explained with given input values -> 0.01193 = 2/(0.66*5.08*50).

FAQ

What is Yawing Moment Coefficient using Wingspan?
The Yawing moment coefficient using wingspan is a moment that lends to rotate an airplane about its vertical axis yawing moment is positive when it tends to turn the plane to the right and negative when it turns the plane to the left and is represented as Cn = Nv/(Qw*S*b) or Yawing moment coefficient = Moment produced by vertical tail/(Wing dynamic pressure*Reference Area*Wingspan). The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft, 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 & The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
How to calculate Yawing Moment Coefficient using Wingspan?
The Yawing moment coefficient using wingspan is a moment that lends to rotate an airplane about its vertical axis yawing moment is positive when it tends to turn the plane to the right and negative when it turns the plane to the left is calculated using Yawing moment coefficient = Moment produced by vertical tail/(Wing dynamic pressure*Reference Area*Wingspan). To calculate Yawing Moment Coefficient using Wingspan, you need Moment produced by vertical tail (Nv), Wing dynamic pressure (Qw), Reference Area (S) & Wingspan (b). With our tool, you need to enter the respective value for Moment produced by vertical tail, Wing dynamic pressure, Reference Area & Wingspan and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Yawing moment coefficient?
In this formula, Yawing moment coefficient uses Moment produced by vertical tail, Wing dynamic pressure, Reference Area & Wingspan. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Yawing moment coefficient = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Wing dynamic pressure)
  • Yawing moment coefficient = Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)
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