Aircraft sideslip velocity for given dihedral angle Calculator

↳

⤿

Static Stability and Control

Aircraft Design

Aircraft Performance

Introduction and Governing Equations

⤿

Lateral Stability

Directional Control

Directional Stability

Lateral Control

Longitudinal Control

Longitudinal Stability

✖Side velocity normal component is the normal component of side velocity associated with the dihedral effect.ⓘ Side Velocity Normal Component [V_n]			+10% -10%
✖The dihedral angle is defined as the spanwise inclination of the wing with respect to the horizontal.ⓘ Dihedral angle [Γ]			+10% -10%

✖Sideslip velocity is the velocity of aircraft when it sideslips.ⓘ Aircraft sideslip velocity for given dihedral angle [V_β]

⎘ Copy

👎

Formula

✖

Aircraft sideslip velocity for given dihedral angle

Formula

`"V"_{"β"} = "V"_{"n"}/sin("Γ")`

Example

`"20.54346m/s"="8m/s"/sin("0.4rad")`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF

Aircraft sideslip velocity for given dihedral angle Solution

STEP 0: Pre-Calculation Summary

Formula Used

Sideslip velocity = Side Velocity Normal Component/sin(Dihedral angle)
V_β = V_n/sin(Γ)
This formula uses 1 Functions, 3 Variables

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

Sideslip velocity - (Measured in Meter per Second) - Sideslip velocity is the velocity of aircraft when it sideslips.
Side Velocity Normal Component - (Measured in Meter per Second) - Side velocity normal component is the normal component of side velocity associated with the dihedral effect.
Dihedral angle - (Measured in Radian) - The dihedral angle is defined as the spanwise inclination of the wing with respect to the horizontal.

STEP 1: Convert Input(s) to Base Unit

Side Velocity Normal Component: 8 Meter per Second --> 8 Meter per Second No Conversion Required
Dihedral angle: 0.4 Radian --> 0.4 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_β = V_n/sin(Γ) --> 8/sin(0.4)

Evaluating ... ...

V_β = 20.5434596443823

STEP 3: Convert Result to Output's Unit

20.5434596443823 Meter per Second --> No Conversion Required

FINAL ANSWER

20.5434596443823 ≈ 20.54346 Meter per Second <-- Sideslip velocity

(Calculation completed in 00.007 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Lateral Stability » Aircraft sideslip velocity for given dihedral angle

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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< 5 Lateral Stability Calculators

Dihedral angle for given sideslip velocity

Go Dihedral angle = asin(Side Velocity Normal Component/Sideslip velocity)

Normal component of aircraft side velocity for given dihedral angle

Go Side Velocity Normal Component = Sideslip velocity*sin(Dihedral angle)

Aircraft sideslip velocity for given dihedral angle

Go Sideslip velocity = Side Velocity Normal Component/sin(Dihedral angle)

Normal component of aircraft side velocity for given forward velocity

Go Side Velocity Normal Component = Local Change in Angle Of Attack*Aircraft Forward Speed

Aircraft forward velocity for given normal component of side velocity

Go Aircraft Forward Speed = Side Velocity Normal Component/Local Change in Angle Of Attack

Aircraft sideslip velocity for given dihedral angle Formula

Sideslip velocity = Side Velocity Normal Component/sin(Dihedral angle)
V_β = V_n/sin(Γ)

What is the effect of too much dihedral effect?

A side effect of too much dihedral effect, caused by excessive dihedral angle among other things, can be yaw-roll coupling (a tendency for an aircraft to Dutch roll). This can be unpleasant to experience, or in extreme conditions, it can lead to loss of control or can overstress an aircraft.

How to Calculate Aircraft sideslip velocity for given dihedral angle?

Aircraft sideslip velocity for given dihedral angle calculator uses Sideslip velocity = Side Velocity Normal Component/sin(Dihedral angle) to calculate the Sideslip velocity, The Aircraft sideslip velocity for given dihedral angle formula is dependent on the normal component of side velocity. Sideslip velocity is denoted by V_β symbol.

How to calculate Aircraft sideslip velocity for given dihedral angle using this online calculator? To use this online calculator for Aircraft sideslip velocity for given dihedral angle, enter Side Velocity Normal Component (V_n) & Dihedral angle (Γ) and hit the calculate button. Here is how the Aircraft sideslip velocity for given dihedral angle calculation can be explained with given input values -> 20.54346 = 8/sin(0.4).

FAQ

What is Aircraft sideslip velocity for given dihedral angle?

The Aircraft sideslip velocity for given dihedral angle formula is dependent on the normal component of side velocity and is represented as V_β = V_n/sin(Γ) or Sideslip velocity = Side Velocity Normal Component/sin(Dihedral angle). Side velocity normal component is the normal component of side velocity associated with the dihedral effect & The dihedral angle is defined as the spanwise inclination of the wing with respect to the horizontal.

How to calculate Aircraft sideslip velocity for given dihedral angle?

The Aircraft sideslip velocity for given dihedral angle formula is dependent on the normal component of side velocity is calculated using Sideslip velocity = Side Velocity Normal Component/sin(Dihedral angle). To calculate Aircraft sideslip velocity for given dihedral angle, you need Side Velocity Normal Component (V_n) & Dihedral angle (Γ). With our tool, you need to enter the respective value for Side Velocity Normal Component & Dihedral angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search