Yawing moment coefficient for given vertical tail volume ratio Solution

STEP 0: Pre-Calculation Summary
Formula Used
Yawing moment coefficient = Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)
Cn = Vv*ηv*Cv*(β+σ)
This formula uses 6 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.
Vertical Tail Volume Ratio - Vertical Tail Volume Ratio relates the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.g., the wing area, and the wingspan.
Vertical tail efficiency - Vertical tail efficiency is the tail efficiency associated with the vertical tail of an aircraft.
Vertical tail Lift curve slope - (Measured in 1 per Radian) - The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.
Sideslip angle - (Measured in Radian) - The sideslip angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.
Sidewash angle - (Measured in Radian) - Sidewash angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.
STEP 1: Convert Input(s) to Base Unit
Vertical Tail Volume Ratio: 1.5 --> No Conversion Required
Vertical tail efficiency: 0.6 --> No Conversion Required
Vertical tail Lift curve slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Sideslip angle: 0.05 Radian --> 0.05 Radian No Conversion Required
Sidewash angle: 0.067 Radian --> 0.067 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Cn = Vvv*Cv*(β+σ) --> 1.5*0.6*0.7*(0.05+0.067)
Evaluating ... ...
Cn = 0.07371
STEP 3: Convert Result to Output's Unit
0.07371 --> No Conversion Required
FINAL ANSWER
0.07371 <-- Yawing moment coefficient
(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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National Institute Of Technology (NIT), Hamirpur
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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 for given vertical tail volume ratio Formula

Yawing moment coefficient = Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)
Cn = Vv*ηv*Cv*(β+σ)

What is a flying wing?

A flying wing is a tailless design that lacks a distinct fuselage, having the pilot, engines, etc., located directly in or on the wing.

How to Calculate Yawing moment coefficient for given vertical tail volume ratio?

Yawing moment coefficient for given vertical tail volume ratio calculator uses Yawing moment coefficient = Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle) to calculate the Yawing moment coefficient, The Yawing moment coefficient for given vertical tail volume ratio is the function of vertical tail efficiency, vertical tail lift curve slope, sideslip angle, and sidewash angle. Yawing moment coefficient is denoted by Cn symbol.

How to calculate Yawing moment coefficient for given vertical tail volume ratio using this online calculator? To use this online calculator for Yawing moment coefficient for given vertical tail volume ratio, enter Vertical Tail Volume Ratio (Vv), Vertical tail efficiency v), Vertical tail Lift curve slope (Cv), Sideslip angle (β) & Sidewash angle (σ) and hit the calculate button. Here is how the Yawing moment coefficient for given vertical tail volume ratio calculation can be explained with given input values -> 0.07371 = 1.5*0.6*0.7*(0.05+0.067).

FAQ

What is Yawing moment coefficient for given vertical tail volume ratio?
The Yawing moment coefficient for given vertical tail volume ratio is the function of vertical tail efficiency, vertical tail lift curve slope, sideslip angle, and sidewash angle and is represented as Cn = Vvv*Cv*(β+σ) or Yawing moment coefficient = Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle). Vertical Tail Volume Ratio relates the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.g., the wing area, and the wingspan, Vertical tail efficiency is the tail efficiency associated with the vertical tail of an aircraft, The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, The sideslip angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind & Sidewash angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.
How to calculate Yawing moment coefficient for given vertical tail volume ratio?
The Yawing moment coefficient for given vertical tail volume ratio is the function of vertical tail efficiency, vertical tail lift curve slope, sideslip angle, and sidewash angle is calculated using Yawing moment coefficient = Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle). To calculate Yawing moment coefficient for given vertical tail volume ratio, you need Vertical Tail Volume Ratio (Vv), Vertical tail efficiency v), Vertical tail Lift curve slope (Cv), Sideslip angle (β) & Sidewash angle (σ). With our tool, you need to enter the respective value for Vertical Tail Volume Ratio, Vertical tail efficiency, Vertical tail Lift curve slope, Sideslip angle & Sidewash angle 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 Vertical Tail Volume Ratio, Vertical tail efficiency, Vertical tail Lift curve slope, Sideslip angle & Sidewash angle. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Yawing moment coefficient = Moment produced by vertical tail/(Wing dynamic pressure*Reference Area*Wingspan)
  • 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)
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