Induced Drag Coefficient given Span Efficiency Factor Calculator

✖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%
✖Span efficiency factor represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio and an elliptical lift distribution.ⓘ Span Efficiency Factor [e_span]			+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.ⓘ Wing Aspect Ratio GLD [AR_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 given Span Efficiency Factor [C_D,i,GLD]

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Induced Drag Coefficient given Span Efficiency Factor Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

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.
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.
Span Efficiency Factor - Span efficiency factor represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio and an elliptical lift distribution.
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.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient GLD: 1.47 --> No Conversion Required
Span Efficiency Factor: 0.95 --> No Conversion Required
Wing Aspect Ratio GLD: 15 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,i,GLD = C_L,GLD^2/(pi*e_span*AR_GLD) --> 1.47^2/(pi*0.95*15)

Evaluating ... ...

C_D,i,GLD = 0.0482691812669862

STEP 3: Convert Result to Output's Unit

0.0482691812669862 --> No Conversion Required

FINAL ANSWER

0.0482691812669862 ≈ 0.048269 <-- Induced Drag Coefficient 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

Induced Drag Coefficient given Span Efficiency Factor Formula

LaTeX Go

Induced Drag Coefficient GLD = Lift Coefficient GLD^2/(pi*Span Efficiency Factor*Wing Aspect Ratio GLD)
C_D,i,GLD = C_L,GLD^2/(pi*e_span*AR_GLD)

Do winglets reduce induced drag?

Winglets increase an aircraft's operating efficiency by reducing what is called induced drag at the tips of the wings. An aircraft's wing is shaped to generate negative pressure on the upper surface and positive pressure on the lower surface as the aircraft moves forward.

How to Calculate Induced Drag Coefficient given Span Efficiency Factor?

Induced Drag Coefficient given Span Efficiency Factor calculator uses Induced Drag Coefficient GLD = Lift Coefficient GLD^2/(pi*Span Efficiency Factor*Wing Aspect Ratio GLD) to calculate the Induced Drag Coefficient GLD, The Induced drag coefficient given span efficiency factor formula calculates the coefficient of induced drag which has been caused due to the element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it. Induced Drag Coefficient GLD is denoted by C_D,i,GLD symbol.

How to calculate Induced Drag Coefficient given Span Efficiency Factor using this online calculator? To use this online calculator for Induced Drag Coefficient given Span Efficiency Factor, enter Lift Coefficient GLD (C_L,GLD), Span Efficiency Factor (e_span) & Wing Aspect Ratio GLD (AR_GLD) and hit the calculate button. Here is how the Induced Drag Coefficient given Span Efficiency Factor calculation can be explained with given input values -> 0.048269 = 1.47^2/(pi*0.95*15).

FAQ

What is Induced Drag Coefficient given Span Efficiency Factor?

The Induced drag coefficient given span efficiency factor formula calculates the coefficient of induced drag which has been caused due to the element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it and is represented as C_D,i,GLD = C_L,GLD^2/(pi*e_span*AR_GLD) or Induced Drag Coefficient GLD = Lift Coefficient GLD^2/(pi*Span Efficiency Factor*Wing Aspect Ratio 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, Span efficiency factor represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio and an elliptical lift distribution & 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.

How to calculate Induced Drag Coefficient given Span Efficiency Factor?

The Induced drag coefficient given span efficiency factor formula calculates the coefficient of induced drag which has been caused due to the element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it is calculated using Induced Drag Coefficient GLD = Lift Coefficient GLD^2/(pi*Span Efficiency Factor*Wing Aspect Ratio GLD). To calculate Induced Drag Coefficient given Span Efficiency Factor, you need Lift Coefficient GLD (C_L,GLD), Span Efficiency Factor (e_span) & Wing Aspect Ratio GLD (AR_GLD). With our tool, you need to enter the respective value for Lift Coefficient GLD, Span Efficiency Factor & Wing Aspect Ratio GLD 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 Induced Drag Coefficient GLD?

In this formula, Induced Drag Coefficient GLD uses Lift Coefficient GLD, Span Efficiency Factor & Wing Aspect Ratio GLD. We can use 1 other way(s) to calculate the same, which is/are as follows -

Induced Drag Coefficient GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Wing Aspect Ratio GLD)

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