Downwash in Elliptical Lift Distribution Calculator

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Two-Dimensional Incompressible Flow

Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

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Lift Distribution

Elementary Flows

Flow and Lift Distribution

Flow over Airfoils and Wings

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Elliptical Lift Distribution

General Lift Distribution

✖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%

✖Downwash is the change in direction of air deflected by the aerodynamic action of an airfoil, wing, or helicopter rotor blade in motion, as part of the process of producing lift.ⓘ Downwash in Elliptical Lift Distribution [w]

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Formula

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Downwash in Elliptical Lift Distribution

Formula

`"w" = -"Γ"_{"o"}/(2*"b")`

Example

`"-2.991453m/s"=-"14m²/s"/(2*"2340mm")`

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Downwash in Elliptical Lift Distribution Solution

STEP 0: Pre-Calculation Summary

Formula Used

Downwash = -Circulation at Origin/(2*Wingspan)
w = -Γ_o/(2*b)
This formula uses 3 Variables

Variables Used

Downwash - (Measured in Meter per Second) - Downwash is the change in direction of air deflected by the aerodynamic action of an airfoil, wing, or helicopter rotor blade in motion, as part of the process of producing lift.
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.

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)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

w = -Γ_o/(2*b) --> -14/(2*2.34)

Evaluating ... ...

w = -2.99145299145299

STEP 3: Convert Result to Output's Unit

-2.99145299145299 Meter per Second --> No Conversion Required

FINAL ANSWER

-2.99145299145299 ≈ -2.991453 Meter per Second <-- Downwash

(Calculation completed in 00.004 seconds)

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< 20 Elliptical Lift Distribution Calculators

Lift at given Distance along Wingspan

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

Circulation at Origin in Elliptical Lift Distribution

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

Coefficient of Lift given Circulation at Origin

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

Freestream Velocity given Circulation at Origin

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

Lift of Wing given Circulation at Origin

Go Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4

Circulation at Origin given Lift of Wing

Go Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi)

Induced Angle of Attack given Coefficient of Lift

Go Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2)

Circulation at given Distance along Wingspan

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

Coefficient of Lift given Induced Drag Coefficient

Go Lift Coefficient ELD = sqrt(pi*Wing Aspect Ratio ELD*Induced Drag Coefficient ELD)

Aspect Ratio given Induced Drag Coefficient

Go Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD)

Induced Drag Coefficient given Aspect Ratio

Go Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD)

Induced Angle of Attack given Circulation at Origin

Go Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity)

Freestream Velocity given Induced Angle of Attack

Go Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack)

Circulation at Origin given Induced Angle of Attack

Go Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity

Induced Angle of Attack given Aspect Ratio

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

Aspect Ratio given Induced Angle of Attack

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

Coefficient of Lift given Induced Angle of Attack

Go Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD

Induced Angle of Attack given Downwash

Go Induced Angle of Attack = -(Downwash/Freestream Velocity)

Downwash in Elliptical Lift Distribution

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

Circulation at Origin given Downwash

Go Circulation at Origin = -2*Downwash*Wingspan

Downwash in Elliptical Lift Distribution Formula

Downwash = -Circulation at Origin/(2*Wingspan)
w = -Γ_o/(2*b)

What is the effect of downwash?

Downwash reduces the wing's effective angle of attack and as a result, reduces lift force and also produces induced drag. Downwash changes the flow field downstream of the main wing and consequently changes the aerodynamic coefficients of the airplane's tail.

How to Calculate Downwash in Elliptical Lift Distribution?

Downwash in Elliptical Lift Distribution calculator uses Downwash = -Circulation at Origin/(2*Wingspan) to calculate the Downwash, The Downwash in elliptical lift distribution formula calculates the downwash which is the change in direction of air deflected by the aerodynamic action of an airfoil. Downwash is denoted by w symbol.

How to calculate Downwash in Elliptical Lift Distribution using this online calculator? To use this online calculator for Downwash in Elliptical Lift Distribution, enter Circulation at Origin (Γ_o) & Wingspan (b) and hit the calculate button. Here is how the Downwash in Elliptical Lift Distribution calculation can be explained with given input values -> -2.991453 = -14/(2*2.34).

FAQ

What is Downwash in Elliptical Lift Distribution?

The Downwash in elliptical lift distribution formula calculates the downwash which is the change in direction of air deflected by the aerodynamic action of an airfoil and is represented as w = -Γ_o/(2*b) or Downwash = -Circulation at Origin/(2*Wingspan). 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.

How to calculate Downwash in Elliptical Lift Distribution?

The Downwash in elliptical lift distribution formula calculates the downwash which is the change in direction of air deflected by the aerodynamic action of an airfoil is calculated using Downwash = -Circulation at Origin/(2*Wingspan). To calculate Downwash in Elliptical Lift Distribution, you need Circulation at Origin (Γ_o) & Wingspan (b). With our tool, you need to enter the respective value for Circulation at Origin & Wingspan and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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