SideSlip Angle for given Yawing Moment Coefficient 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 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 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%
✖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 [σ]			+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 for given Yawing Moment Coefficient [β]

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SideSlip Angle for given Yawing Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Sideslip Angle = (Yawing Moment Coefficient/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope/(Reference Area*Wingspan*Wing Dynamic Pressure)))-Sidewash Angle
β = (C_n/(𝒍_v*S_v*Q_v*C_v/(S*b*Q_w)))-σ
This formula uses 10 Variables

Variables Used

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.
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 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.
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.
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

Yawing Moment Coefficient: 1.4 --> 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
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
Sidewash Angle: 0.067 Radian --> 0.067 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

β = (C_n/(𝒍_v*S_v*Q_v*C_v/(S*b*Q_w)))-σ --> (1.4/(1.2*5*11*0.7/(5.08*1.15*0.66)))-0.067

Evaluating ... ...

β = 0.04984

STEP 3: Convert Result to Output's Unit

0.04984 Radian --> No Conversion Required

FINAL ANSWER

0.04984 Radian <-- Sideslip Angle

(Calculation completed in 00.020 seconds)

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

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< 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

SideSlip Angle for given Yawing Moment Coefficient Formula

LaTeX Go

Is slip desired while flying?

Flying in a slip is aerodynamically inefficient since the lift-to-drag ratio is reduced. More drag is at play consuming energy but not producing lift.

How to Calculate SideSlip Angle for given Yawing Moment Coefficient?

SideSlip Angle for given Yawing Moment Coefficient calculator uses Sideslip Angle = (Yawing Moment Coefficient/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope/(Reference Area*Wingspan*Wing Dynamic Pressure)))-Sidewash Angle to calculate the Sideslip Angle, SideSlip Angle for given Yawing Moment Coefficient is a measure of the angle between the aircraft's direction of motion and its direction of symmetry, calculated based on the yawing moment coefficient, vertical tail moment arm, vertical tail area, vertical tail dynamic pressure, vertical tail lift curve slope, reference area, wingspan and wing dynamic pressure, with consideration of the sidewash angle. Sideslip Angle is denoted by β symbol.

How to calculate SideSlip Angle for given Yawing Moment Coefficient using this online calculator? To use this online calculator for SideSlip Angle for given Yawing Moment Coefficient, enter Yawing Moment Coefficient (C_n), Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v), Reference Area (S), Wingspan (b), Wing Dynamic Pressure (Q_w) & Sidewash Angle (σ) and hit the calculate button. Here is how the SideSlip Angle for given Yawing Moment Coefficient calculation can be explained with given input values -> 0.04984 = (1.4/(1.2*5*11*0.7/(5.08*1.15*0.66)))-0.067.

FAQ

What is SideSlip Angle for given Yawing Moment Coefficient?

SideSlip Angle for given Yawing Moment Coefficient is a measure of the angle between the aircraft's direction of motion and its direction of symmetry, calculated based on the yawing moment coefficient, vertical tail moment arm, vertical tail area, vertical tail dynamic pressure, vertical tail lift curve slope, reference area, wingspan and wing dynamic pressure, with consideration of the sidewash angle and is represented as β = (C_n/(𝒍_v*S_v*Q_v*C_v/(S*b*Q_w)))-σ or Sideslip Angle = (Yawing Moment Coefficient/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope/(Reference Area*Wingspan*Wing Dynamic Pressure)))-Sidewash Angle. Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, 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 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 & 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 SideSlip Angle for given Yawing Moment Coefficient?

SideSlip Angle for given Yawing Moment Coefficient is a measure of the angle between the aircraft's direction of motion and its direction of symmetry, calculated based on the yawing moment coefficient, vertical tail moment arm, vertical tail area, vertical tail dynamic pressure, vertical tail lift curve slope, reference area, wingspan and wing dynamic pressure, with consideration of the sidewash angle is calculated using Sideslip Angle = (Yawing Moment Coefficient/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope/(Reference Area*Wingspan*Wing Dynamic Pressure)))-Sidewash Angle. To calculate SideSlip Angle for given Yawing Moment Coefficient, you need Yawing Moment Coefficient (C_n), Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v), Reference Area (S), Wingspan (b), Wing Dynamic Pressure (Q_w) & Sidewash Angle (σ). With our tool, you need to enter the respective value for Yawing Moment Coefficient, Vertical Tail Moment Arm, Vertical Tail Area, Vertical Tail Dynamic Pressure, Vertical Tail Lift Curve Slope, Reference Area, Wingspan, Wing Dynamic Pressure & 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 Sideslip Angle?

In this formula, Sideslip Angle uses Yawing Moment Coefficient, Vertical Tail Moment Arm, Vertical Tail Area, Vertical Tail Dynamic Pressure, Vertical Tail Lift Curve Slope, Reference Area, Wingspan, Wing Dynamic Pressure & Sidewash Angle. We can use 3 other way(s) to calculate the same, which is/are as follows -

Sideslip Angle = Vertical Tail Angle of Attack-Sidewash Angle
Sideslip Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sidewash Angle
Sideslip Angle = (Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Efficiency*Vertical Tail Lift Curve Slope))-Sidewash Angle

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