Aspect Ratio given Induced Angle of Attack Solution

STEP 0: Pre-Calculation Summary
Formula Used
Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack)
ARELD = CL,ELD/(pi*αi)
This formula uses 1 Constants, 3 Variables
Constants Used
pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288
Variables Used
Wing Aspect Ratio ELD - Wing Aspect Ratio ELD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.
Lift Coefficient ELD - The Lift Coefficient ELD is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
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
Lift Coefficient ELD: 1.49 --> No Conversion Required
Induced Angle of Attack: 11 Degree --> 0.19198621771934 Radian (Check conversion here)
STEP 2: Evaluate Formula
Substituting Input Values in Formula
ARELD = CL,ELD/(pi*αi) --> 1.49/(pi*0.19198621771934)
Evaluating ... ...
ARELD = 2.47039467753456
STEP 3: Convert Result to Output's Unit
2.47039467753456 --> No Conversion Required
FINAL ANSWER
2.47039467753456 2.470395 <-- Wing Aspect Ratio ELD
(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

Aspect Ratio given Induced Angle of Attack Formula

Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack)
ARELD = CL,ELD/(pi*αi)

How does aspect ratio affect aircraft performance?

The ratio of the length of wings to their width is called the aspect ratio. A high aspect ratio indicates long, narrow wings. Generally, high aspect ratio wings give slightly more lift and enable sustained, endurance flight, while low aspect ratio wings are best for swift maneuverability.

How to Calculate Aspect Ratio given Induced Angle of Attack?

Aspect Ratio given Induced Angle of Attack calculator uses Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack) to calculate the Wing Aspect Ratio ELD, The Aspect ratio given induced angle of attack formula calculates the aspect ratio of the wing by using the induced angle of attack and the coefficient of lift. Wing Aspect Ratio ELD is denoted by ARELD symbol.

How to calculate Aspect Ratio given Induced Angle of Attack using this online calculator? To use this online calculator for Aspect Ratio given Induced Angle of Attack, enter Lift Coefficient ELD (CL,ELD) & Induced Angle of Attack i) and hit the calculate button. Here is how the Aspect Ratio given Induced Angle of Attack calculation can be explained with given input values -> 2.486975 = 1.49/(pi*0.19198621771934).

FAQ

What is Aspect Ratio given Induced Angle of Attack?
The Aspect ratio given induced angle of attack formula calculates the aspect ratio of the wing by using the induced angle of attack and the coefficient of lift and is represented as ARELD = CL,ELD/(pi*αi) or Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack). The Lift Coefficient ELD is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area & The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.
How to calculate Aspect Ratio given Induced Angle of Attack?
The Aspect ratio given induced angle of attack formula calculates the aspect ratio of the wing by using the induced angle of attack and the coefficient of lift is calculated using Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack). To calculate Aspect Ratio given Induced Angle of Attack, you need Lift Coefficient ELD (CL,ELD) & Induced Angle of Attack i). With our tool, you need to enter the respective value for Lift Coefficient ELD & 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 Wing Aspect Ratio ELD?
In this formula, Wing Aspect Ratio ELD uses Lift Coefficient ELD & Induced Angle of Attack. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD)
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