Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 200+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Dynamic pressure at wing for given yawing moment coefficient
Wing dynamic pressure=Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Yawing moment coefficient) GO
Wingspan for given yawing moment coefficient
Wingspan=Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Yawing moment coefficient*Wing dynamic pressure) GO
Vertical tail moment arm for given lift curve slope
Vertical tail moment arm=Moment produced by vertical tail/(Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area) GO
Vertical tail lift curve slope for given moment
Vertical tail Lift curve slope=Moment produced by vertical tail/(Vertical tail moment arm*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area) GO
Moment produced by vertical tail for given lift curve slope
Moment produced by vertical tail=Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area GO
Vertical tail dynamic pressure for given vertical tail side force
Vertical tail dynamic pressure=-Vertical tail side force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area) GO
Vertical tail area for given vertical tail side force
Vertical tail area=-Vertical tail side force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail dynamic pressure) GO
Vertical tail lift curve slope
Vertical tail Lift curve slope=-Vertical tail side force/(Vertical tail angle of attack*Vertical tail dynamic pressure*Vertical tail area) GO
Vertical tail Side force
Vertical tail side force=-Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area*Vertical tail dynamic pressure GO
Vertical tail angle of attack
Vertical tail angle of attack=Sidewash angle+Sideslip angle GO
Sideslip angle
Sideslip angle=Vertical tail angle of attack-Sidewash angle GO

3 Other formulas that calculate the same Output

Sidewash angle for given yawing moment coefficient
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 GO
Sidewash angle for given moment produced by vertical tail
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 GO
Sidewash angle for given yawing moment coefficient
Sidewash angle=(Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sideslip angle GO

Sidewash angle Formula

Sidewash angle=Vertical tail angle of attack-Sideslip angle
σ=α<sub>v</sub>-β
More formulas
Vertical tail angle of attack GO
Sideslip angle GO
Vertical tail Side force GO
Vertical tail lift curve slope GO
Vertical tail angle of attack for given vertical tail side force GO
Vertical tail dynamic pressure for given vertical tail side force GO
Vertical tail area for given vertical tail side force GO
Moment produced by vertical tail for given side force GO
Vertical tail moment arm for given side force GO
Vertical tail side force for given moment GO
Moment produced by vertical tail for given lift curve slope GO
Vertical tail moment arm for given lift curve slope GO
Vertical tail lift curve slope for given moment GO
Sideslip angle for given moment produced by vertical tail GO

What is the difference between a sideslip and a forward slip?

A forward slip is used for losing altitude. A sideslip is defined to be a slip where the fuselage is parallel to the line of travel. A sideslip is used for landing in a crosswind.

How to Calculate Sidewash angle?

Sidewash angle calculator uses Sidewash angle=Vertical tail angle of attack-Sideslip angle to calculate the Sidewash angle, The Sidewash angle for an aircraft is the difference between the vertical tail angle of attack and sideslip angle. . Sidewash angle and is denoted by σ symbol.

How to calculate Sidewash angle using this online calculator? To use this online calculator for Sidewash angle, enter Vertical tail angle of attack v) and Sideslip angle (β) and hit the calculate button. Here is how the Sidewash angle calculation can be explained with given input values -> 0.14 = 0.19-0.05.

FAQ

What is Sidewash angle?
The Sidewash angle for an aircraft is the difference between the vertical tail angle of attack and sideslip angle. and is represented as σ=αv or Sidewash angle=Vertical tail angle of attack-Sideslip angle. Vertical tail angle of attack is the angle of attack experienced by the vertical tailplane of an aircraft and 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.
How to calculate Sidewash angle?
The Sidewash angle for an aircraft is the difference between the vertical tail angle of attack and sideslip angle. is calculated using Sidewash angle=Vertical tail angle of attack-Sideslip angle. To calculate Sidewash angle, you need Vertical tail angle of attack v) and Sideslip angle (β). With our tool, you need to enter the respective value for Vertical tail angle of attack and Sideslip 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 Sidewash angle?
In this formula, Sidewash angle uses Vertical tail angle of attack and Sideslip angle. We can use 3 other way(s) to calculate the same, which is/are as follows -
  • 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=(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
  • Sidewash angle=(Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sideslip angle
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