Aspect Ratio given Induced Drag Coefficient Calculator

⤿

Two-Dimensional Incompressible Flow

Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

⤿

Lift Distribution

Elementary Flows

Flow and Lift Distribution

Flow over Airfoils and Wings

⤿

Elliptical Lift Distribution

General Lift Distribution

✖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.ⓘ Lift Coefficient ELD [C_L,ELD]			+10% -10%
✖The Induced Drag Coefficient ELD is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.ⓘ Induced Drag Coefficient ELD [C_D,i,ELD]			+10% -10%

✖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.ⓘ Aspect Ratio given Induced Drag Coefficient [AR_ELD]

⎘ Copy

👎

Formula

✖

Aspect Ratio given Induced Drag Coefficient

Formula

`"AR"_{"ELD"} = "C"_{"L,ELD"}^2/(pi*"C"_{"D,i,ELD"})`

Example

`"2.453749"=("1.49")^2/(pi*"0.288")`

Calculator

LaTeX

Reset

👍

Download Elliptical Lift Distribution Formulas PDF PDF Image

Aspect Ratio given Induced Drag Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD)
AR_ELD = C_L,ELD^2/(pi*C_D,i,ELD)
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 Drag Coefficient ELD - The Induced Drag Coefficient ELD is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient ELD: 1.49 --> No Conversion Required
Induced Drag Coefficient ELD: 0.288 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

AR_ELD = C_L,ELD^2/(pi*C_D,i,ELD) --> 1.49^2/(pi*0.288)

Evaluating ... ...

AR_ELD = 2.45374923026609

STEP 3: Convert Result to Output's Unit

2.45374923026609 --> No Conversion Required

FINAL ANSWER

2.45374923026609 ≈ 2.453749 <-- Wing Aspect Ratio ELD

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aerodynamics » Two-Dimensional Incompressible Flow » Lift Distribution » Elliptical Lift Distribution » Aspect Ratio given Induced Drag Coefficient

Credits

Created by Ravi Khiyani

Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore

Ravi Khiyani has created this Calculator and 200+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< 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 Drag Coefficient Formula

Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD)
AR_ELD = C_L,ELD^2/(pi*C_D,i,ELD)

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 Drag Coefficient?

Aspect Ratio given Induced Drag Coefficient calculator uses Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD) to calculate the Wing Aspect Ratio ELD, The Aspect ratio given induced drag coefficient formula calculates the aspect ratio of the wing by using the induced drag coefficient and the coefficient of lift. Wing Aspect Ratio ELD is denoted by AR_ELD symbol.

How to calculate Aspect Ratio given Induced Drag Coefficient using this online calculator? To use this online calculator for Aspect Ratio given Induced Drag Coefficient, enter Lift Coefficient ELD (C_L,ELD) & Induced Drag Coefficient ELD (C_D,i,ELD) and hit the calculate button. Here is how the Aspect Ratio given Induced Drag Coefficient calculation can be explained with given input values -> 2.486796 = 1.49^2/(pi*0.288).

FAQ

What is Aspect Ratio given Induced Drag Coefficient?

The Aspect ratio given induced drag coefficient formula calculates the aspect ratio of the wing by using the induced drag coefficient and the coefficient of lift and is represented as AR_ELD = C_L,ELD^2/(pi*C_D,i,ELD) or Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag 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 & The Induced Drag Coefficient ELD is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.

How to calculate Aspect Ratio given Induced Drag Coefficient?

The Aspect ratio given induced drag coefficient formula calculates the aspect ratio of the wing by using the induced drag coefficient and the coefficient of lift is calculated using Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD). To calculate Aspect Ratio given Induced Drag Coefficient, you need Lift Coefficient ELD (C_L,ELD) & Induced Drag Coefficient ELD (C_D,i,ELD). With our tool, you need to enter the respective value for Lift Coefficient ELD & Induced Drag Coefficient ELD 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 Drag Coefficient ELD. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

Home

FREE PDFs

🔍 Search