Sidewash Angle given Yawing Moment Coefficient using Wingspan Calculator

✖Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.ⓘ Yawing Moment Coefficient [C_n]			+10% -10%
✖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.ⓘ Reference Area [S]			+10% -10%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+10% -10%
✖Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing Dynamic Pressure [Q_w]			+10% -10%
✖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 Moment Arm [𝒍_v]			+10% -10%
✖The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.ⓘ Vertical Tail Area [S_v]			+10% -10%
✖Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical Tail Dynamic Pressure [Q_v]			+10% -10%
✖The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.ⓘ Vertical Tail Lift Curve Slope [C_v]			+10% -10%
✖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.ⓘ Sideslip Angle [β]			+10% -10%

✖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.ⓘ Sidewash Angle given Yawing Moment Coefficient using Wingspan [σ]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Aerodynamic Parameters Formulas PDF PDF Image

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 = (C_n*S*b*Q_w/(𝒍_v*S_v*Q_v*C_v))-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: 1.15 Meter --> 1.15 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 = (C_n*S*b*Q_w/(𝒍_v*S_v*Q_v*C_v))-β --> (1.4*5.08*1.15*0.66/(1.2*5*11*0.7))-0.05

Evaluating ... ...

σ = 0.06684

STEP 3: Convert Result to Output's Unit

0.06684 Radian --> No Conversion Required

FINAL ANSWER

0.06684 Radian <-- Sidewash Angle

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Aerospace » Aerodynamic Parameters » Sidewash Angle given Yawing Moment Coefficient using Wingspan

Credits

Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< Aerodynamic Parameters Calculators

Sidewash Angle for given Moment Produced by Vertical Tail

LaTeX Go Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle

Yawing Moment Coefficient using Wingspan

LaTeX Go Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan)

Sideslip Angle for Aircraft

LaTeX Go Sideslip Angle = Vertical Tail Angle of Attack-Sidewash Angle

Sidewash angle

LaTeX Go Sidewash Angle = Vertical Tail Angle of Attack-Sideslip Angle

Sidewash Angle given Yawing Moment Coefficient using Wingspan Formula

LaTeX Go

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 measure of the angle between the vertical stabilizer and the horizontal stabilizer of an aircraft, calculated by considering the yawing moment coefficient, reference area, wingspan, wing dynamic pressure, vertical tail moment arm, vertical tail area, vertical tail dynamic pressure, and vertical tail lift curve slope, providing a critical parameter for aircraft stability and control analysis. 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 (C_n), Reference Area (S), Wingspan (b), Wing Dynamic Pressure (Q_w), Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v) & 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 -> 0.06684 = (1.4*5.08*1.15*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 measure of the angle between the vertical stabilizer and the horizontal stabilizer of an aircraft, calculated by considering the yawing moment coefficient, reference area, wingspan, wing dynamic pressure, vertical tail moment arm, vertical tail area, vertical tail dynamic pressure, and vertical tail lift curve slope, providing a critical parameter for aircraft stability and control analysis and is represented as σ = (C_n*S*b*Q_w/(𝒍_v*S_v*Q_v*C_v))-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 measure of the angle between the vertical stabilizer and the horizontal stabilizer of an aircraft, calculated by considering the yawing moment coefficient, reference area, wingspan, wing dynamic pressure, vertical tail moment arm, vertical tail area, vertical tail dynamic pressure, and vertical tail lift curve slope, providing a critical parameter for aircraft stability and control analysis 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 (C_n), Reference Area (S), Wingspan (b), Wing Dynamic Pressure (Q_w), Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v) & 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 = (Vertical Tail Moment/(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

Home

FREE PDFs

🔍 Search