Sidewash Angle given Yawing Moment Coefficient using Wingspan Solution

STEP 0: Pre-Calculation Summary
Formula Used
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
σ = (Cn*S*b*Qw/(𝒍v*Sv*Qv*Cv))-β
This formula uses 10 Variables
Variables Used
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.
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.
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.
Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.
Vertical tail moment arm - (Measured in Meter) - The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Vertical tail area - (Measured in Square Meter) - The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.
Vertical tail dynamic pressure - (Measured in Pascal) - Vertical tail dynamic pressure is the dynamic pressure 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.
STEP 1: Convert Input(s) to Base Unit
Yawing moment coefficient: 1.4 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 50 Meter --> 50 Meter No Conversion Required
Wing dynamic pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Vertical tail moment arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical tail area: 5 Square Meter --> 5 Square Meter No Conversion Required
Vertical tail dynamic pressure: 11 Pascal --> 11 Pascal 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
STEP 2: Evaluate Formula
Substituting Input Values in Formula
σ = (Cn*S*b*Qw/(𝒍v*Sv*Qv*Cv))-β --> (1.4*5.08*50*0.66/(1.2*5*11*0.7))-0.05
Evaluating ... ...
σ = 5.03
STEP 3: Convert Result to Output's Unit
5.03 Radian --> No Conversion Required
FINAL ANSWER
5.03 Radian <-- Sidewash angle
(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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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

Sidewash Angle given Yawing Moment Coefficient using Wingspan Formula

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
σ = (Cn*S*b*Qw/(𝒍v*Sv*Qv*Cv))-β

How a slip affects flight?

When an aircraft is put into a forward slip with no other changes to the throttle or elevator, the pilot will notice an increased descent rate (or reduced rate of ascent). This is usually mostly due to increased drag on the fuselage. The airflow over the fuselage is at a sideways angle, increasing the relative frontal area, which increases drag.

How to Calculate Sidewash Angle given Yawing Moment Coefficient using Wingspan?

Sidewash Angle given Yawing Moment Coefficient using Wingspan calculator uses 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 to calculate the Sidewash angle, Sidewash Angle given Yawing Moment Coefficient using Wingspan is a function of the vertical tail's moment arm, lift curve slope, dynamic pressure (at vertical tail), area, sideslip angle, wing's reference area, wingspan, and dynamic pressure at wing. Sidewash angle is denoted by σ symbol.

How to calculate Sidewash Angle given Yawing Moment Coefficient using Wingspan using this online calculator? To use this online calculator for Sidewash Angle given Yawing Moment Coefficient using Wingspan, enter Yawing moment coefficient (Cn), Reference Area (S), Wingspan (b), Wing dynamic pressure (Qw), Vertical tail moment arm (𝒍v), Vertical tail area (Sv), Vertical tail dynamic pressure (Qv), Vertical tail Lift curve slope (Cv) & Sideslip angle (β) and hit the calculate button. Here is how the Sidewash Angle given Yawing Moment Coefficient using Wingspan calculation can be explained with given input values -> 5.03 = (1.4*5.08*50*0.66/(1.2*5*11*0.7))-0.05.

FAQ

What is Sidewash Angle given Yawing Moment Coefficient using Wingspan?
Sidewash Angle given Yawing Moment Coefficient using Wingspan is a function of the vertical tail's moment arm, lift curve slope, dynamic pressure (at vertical tail), area, sideslip angle, wing's reference area, wingspan, and dynamic pressure at wing and is represented as σ = (Cn*S*b*Qw/(𝒍v*Sv*Qv*Cv))-β or 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. Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, 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, Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft, The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, Vertical tail dynamic pressure is the dynamic pressure 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.
How to calculate Sidewash Angle given Yawing Moment Coefficient using Wingspan?
Sidewash Angle given Yawing Moment Coefficient using Wingspan is a function of the vertical tail's moment arm, lift curve slope, dynamic pressure (at vertical tail), area, sideslip angle, wing's reference area, wingspan, and dynamic pressure at wing is calculated using 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. To calculate Sidewash Angle given Yawing Moment Coefficient using Wingspan, you need Yawing moment coefficient (Cn), Reference Area (S), Wingspan (b), Wing dynamic pressure (Qw), Vertical tail moment arm (𝒍v), Vertical tail area (Sv), Vertical tail dynamic pressure (Qv), Vertical tail Lift curve slope (Cv) & Sideslip angle (β). With our tool, you need to enter the respective value for 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 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 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. We can use 3 other way(s) to calculate the same, which is/are as follows -
  • Sidewash angle = Vertical tail angle of attack-Sideslip angle
  • 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/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sideslip angle
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