Freestream Velocity given Induced Angle of Attack Calculator

✖Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.ⓘ Circulation at Origin [Γ_o]			+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%
✖The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.ⓘ Induced Angle of Attack [α_i]			+10% -10%

✖The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.ⓘ Freestream Velocity given Induced Angle of Attack [V_∞]

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Freestream Velocity given Induced Angle of Attack Solution

STEP 0: Pre-Calculation Summary

Formula Used

Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack)
V_∞ = Γ_o/(2*b*α_i)
This formula uses 4 Variables

Variables Used

Freestream Velocity - (Measured in Meter per Second) - The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.
Circulation at Origin - (Measured in Square Meter per Second) - Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.
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.
Induced Angle of Attack - (Measured in Radian) - The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.

STEP 1: Convert Input(s) to Base Unit

Circulation at Origin: 14 Square Meter per Second --> 14 Square Meter per Second No Conversion Required
Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)
Induced Angle of Attack: 11 Degree --> 0.19198621771934 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_∞ = Γ_o/(2*b*α_i) --> 14/(2*2.34*0.19198621771934)

Evaluating ... ...

V_∞ = 15.5816028201885

STEP 3: Convert Result to Output's Unit

15.5816028201885 Meter per Second --> No Conversion Required

FINAL ANSWER

15.5816028201885 ≈ 15.5816 Meter per Second <-- Freestream Velocity

(Calculation completed in 00.005 seconds)

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< Elliptical Lift Distribution Calculators

Lift at given Distance along Wingspan

LaTeX Go Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)

Circulation at given Distance along Wingspan

LaTeX Go Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)

Induced Angle of Attack given Aspect Ratio

LaTeX Go Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD)

Downwash in Elliptical Lift Distribution

LaTeX Go Downwash = -Circulation at Origin/(2*Wingspan)

Freestream Velocity given Induced Angle of Attack Formula

LaTeX Go

Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack)
V_∞ = Γ_o/(2*b*α_i)

Why is an elliptical lift distribution ideal?

The energy in that vortex appears to the aircraft as 'lift induced drag'. The aerodynamicist tries to design the tip to keep induced drag low. An elliptical lift distribution is best for this purpose. The shape producing this varies with speed, altitude, and other factors, so tips vary from design to design.

How to Calculate Freestream Velocity given Induced Angle of Attack?

Freestream Velocity given Induced Angle of Attack calculator uses Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack) to calculate the Freestream Velocity, The Freestream velocity given induced angle of attack formula calculates the velocity of the fluid flowing around the wing when the induced angle of attack of the wing is given. Freestream Velocity is denoted by V_∞ symbol.

How to calculate Freestream Velocity given Induced Angle of Attack using this online calculator? To use this online calculator for Freestream Velocity given Induced Angle of Attack, enter Circulation at Origin (Γ_o), Wingspan (b) & Induced Angle of Attack (α_i) and hit the calculate button. Here is how the Freestream Velocity given Induced Angle of Attack calculation can be explained with given input values -> 15.5816 = 14/(2*2.34*0.19198621771934).

FAQ

What is Freestream Velocity given Induced Angle of Attack?

The Freestream velocity given induced angle of attack formula calculates the velocity of the fluid flowing around the wing when the induced angle of attack of the wing is given and is represented as V_∞ = Γ_o/(2*b*α_i) or Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack). Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip & The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.

How to calculate Freestream Velocity given Induced Angle of Attack?

The Freestream velocity given induced angle of attack formula calculates the velocity of the fluid flowing around the wing when the induced angle of attack of the wing is given is calculated using Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack). To calculate Freestream Velocity given Induced Angle of Attack, you need Circulation at Origin (Γ_o), Wingspan (b) & Induced Angle of Attack (α_i). With our tool, you need to enter the respective value for Circulation at Origin, Wingspan & Induced Angle of Attack 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 Freestream Velocity?

In this formula, Freestream Velocity uses Circulation at Origin, Wingspan & Induced Angle of Attack. We can use 1 other way(s) to calculate the same, which is/are as follows -

Freestream Velocity = pi*Wingspan*Circulation at Origin/(2*Reference Area Origin*Lift Coefficient ELD)

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