Aspect Ratio given Induced Drag Factor Calculator

✖The Induced Drag Factor is a function of the Fourier series constants which has been used for the general circulation distribution expression for the finite wing.ⓘ Induced Drag Factor [δ]			+10% -10%
✖The Lift Coefficient GLD 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 GLD [C_L,GLD]			+10% -10%
✖The Induced Drag Coefficient GLD is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.ⓘ Induced Drag Coefficient GLD [C_D,i,GLD]			+10% -10%

✖Wing Aspect Ratio GLD 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 Factor [AR_GLD]

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Aspect Ratio given Induced Drag Factor Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing Aspect Ratio GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Induced Drag Coefficient GLD)
AR_GLD = ((1+δ)*C_L,GLD^2)/(pi*C_D,i,GLD)
This formula uses 1 Constants, 4 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Wing Aspect Ratio GLD - Wing Aspect Ratio GLD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.
Induced Drag Factor - The Induced Drag Factor is a function of the Fourier series constants which has been used for the general circulation distribution expression for the finite wing.
Lift Coefficient GLD - The Lift Coefficient GLD 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 GLD - The Induced Drag Coefficient GLD 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

Induced Drag Factor: 0.05 --> No Conversion Required
Lift Coefficient GLD: 1.47 --> No Conversion Required
Induced Drag Coefficient GLD: 0.048 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

AR_GLD = ((1+δ)*C_L,GLD^2)/(pi*C_D,i,GLD) --> ((1+0.05)*1.47^2)/(pi*0.048)

Evaluating ... ...

AR_GLD = 15.0464088480684

STEP 3: Convert Result to Output's Unit

15.0464088480684 --> No Conversion Required

FINAL ANSWER

15.0464088480684 ≈ 15.04641 <-- Wing Aspect Ratio GLD

(Calculation completed in 00.004 seconds)

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< General Lift Distribution Calculators

Lift Coefficient given Span Efficiency Factor

LaTeX Go Lift Coefficient GLD = sqrt(pi*Span Efficiency Factor*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)

Induced Drag Coefficient given Span Efficiency Factor

LaTeX Go Induced Drag Coefficient GLD = Lift Coefficient GLD^2/(pi*Span Efficiency Factor*Wing Aspect Ratio GLD)

Span Efficiency Factor

LaTeX Go Span Efficiency Factor = (1+Induced Drag Factor)^(-1)

Induced Drag Factor given Span Efficiency Factor

LaTeX Go Induced Drag Factor = Span Efficiency Factor^(-1)-1

Aspect Ratio given Induced Drag Factor Formula

LaTeX Go

Wing Aspect Ratio GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Induced Drag Coefficient GLD)
AR_GLD = ((1+δ)*C_L,GLD^2)/(pi*C_D,i,GLD)

How does aspect ratio affect aircraft?

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 Factor?

Aspect Ratio given Induced Drag Factor calculator uses Wing Aspect Ratio GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Induced Drag Coefficient GLD) to calculate the Wing Aspect Ratio GLD, The Aspect ratio given induced drag factor formula calculates the aspect ratio of the wing for the actual lift distribution which is a function of the Fourier series, by using the induced drag factor. Wing Aspect Ratio GLD is denoted by AR_GLD symbol.

How to calculate Aspect Ratio given Induced Drag Factor using this online calculator? To use this online calculator for Aspect Ratio given Induced Drag Factor, enter Induced Drag Factor (δ), Lift Coefficient GLD (C_L,GLD) & Induced Drag Coefficient GLD (C_D,i,GLD) and hit the calculate button. Here is how the Aspect Ratio given Induced Drag Factor calculation can be explained with given input values -> 18.05569 = ((1+0.05)*1.47^2)/(pi*0.048).

FAQ

What is Aspect Ratio given Induced Drag Factor?

The Aspect ratio given induced drag factor formula calculates the aspect ratio of the wing for the actual lift distribution which is a function of the Fourier series, by using the induced drag factor and is represented as AR_GLD = ((1+δ)*C_L,GLD^2)/(pi*C_D,i,GLD) or Wing Aspect Ratio GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Induced Drag Coefficient GLD). The Induced Drag Factor is a function of the Fourier series constants which has been used for the general circulation distribution expression for the finite wing, The Lift Coefficient GLD 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 GLD 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 Factor?

The Aspect ratio given induced drag factor formula calculates the aspect ratio of the wing for the actual lift distribution which is a function of the Fourier series, by using the induced drag factor is calculated using Wing Aspect Ratio GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Induced Drag Coefficient GLD). To calculate Aspect Ratio given Induced Drag Factor, you need Induced Drag Factor (δ), Lift Coefficient GLD (C_L,GLD) & Induced Drag Coefficient GLD (C_D,i,GLD). With our tool, you need to enter the respective value for Induced Drag Factor, Lift Coefficient GLD & Induced Drag Coefficient GLD 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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