Coefficient of Drag due to lift Calculator

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Introduction and Governing Equations

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Lift and Drag Polar

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✖The Lift Coefficient 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 [C_L]			+10% -10%
✖The Oswald efficiency factor is a correction factor that 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.ⓘ Oswald Efficiency Factor [e_oswald]			+10% -10%
✖The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.ⓘ Aspect Ratio of a wing [AR]			+10% -10%

✖The Coefficient of drag due to lift is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attack.ⓘ Coefficient of Drag due to lift [C_D,i]

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Formula

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Coefficient of Drag due to lift

Formula

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

Example

`"0.192577"=(("1.1")^2)/(pi*"0.5"*"4")`

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Coefficient of Drag due to lift Solution

STEP 0: Pre-Calculation Summary

Formula Used

Coefficient of drag due to lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)
C_D,i = (C_L^2)/(pi*e_oswald*AR)
This formula uses 1 Constants, 4 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Coefficient of drag due to lift - The Coefficient of drag due to lift is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attack.
Lift Coefficient - The Lift Coefficient 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.
Oswald Efficiency Factor - The Oswald efficiency factor is a correction factor that 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.
Aspect Ratio of a wing - The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient: 1.1 --> No Conversion Required
Oswald Efficiency Factor: 0.5 --> No Conversion Required
Aspect Ratio of a wing: 4 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,i = (C_L^2)/(pi*e_oswald*AR) --> (1.1^2)/(pi*0.5*4)

Evaluating ... ...

C_D,i = 0.192577481141193

STEP 3: Convert Result to Output's Unit

0.192577481141193 --> No Conversion Required

FINAL ANSWER

0.192577481141193 ≈ 0.192577 <-- Coefficient of drag due to lift

(Calculation completed in 00.004 seconds)

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Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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< 21 Lift and Drag Polar Calculators

Drag Coefficient for given zero-lift drag coefficient

Go Drag Coefficient = Zero-lift drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Drag Coefficient for given parasite drag coefficient

Go Drag Coefficient = Parasite Drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Coefficient of Drag due to lift

Go Coefficient of drag due to lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)

Modern Lift Equation

Go Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2

Induced drag given span efficiency factor

Go Induced Drag = Drag Coefficient*Density of Material*Velocity^2*Reference Area/2

Lift given induced drag

Go Lift Force = sqrt(Induced Drag*3.14*Dynamic Pressure*Lateral plane span^2)

Induced Drag for Wings having Elliptic Lift Distribution

Go Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral plane span^2)

Coefficient of lift given drag

Go Lift Coefficient = (Gross Weight*Drag Coefficient)/Drag Force

Coefficient of drag given drag

Go Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight

Drag

Go Drag Force = Gross Weight/Lift Coefficient/Drag Coefficient

Lift coefficient given drag coefficient

Go Lift Coefficient = Lift Force/Drag Force*Drag Coefficient

Drag coefficient given lift coefficient

Go Drag Coefficient = Lift Coefficient*Drag Force/Lift Force

Lift given drag coefficient

Go Lift Force = Lift Coefficient/Drag Coefficient*Drag Force

Drag given lift coefficient

Go Drag Force = Lift Force*Drag Coefficient/Lift Coefficient

Parasite Drag Coefficient at zero lift

Go Zero-lift drag coefficient = Drag Coefficient-Coefficient of drag due to lift

Lift given lift coefficient

Go Lift Force = Lift Coefficient*Dynamic Pressure

Drag given drag coefficient

Go Drag Force = Drag Coefficient*Dynamic Pressure

Lift coefficient new

Go Lift Coefficient = Lift Force/Dynamic Pressure

Drag coefficient new

Go Drag Coefficient = Drag Force/Dynamic Pressure

Lift given aerodynamic force

Go Lift Force = Aerodynamic Force-Drag Force

Drag given aerodynamic force

Go Drag Force = Aerodynamic Force-Lift Force

Coefficient of Drag due to lift Formula

Coefficient of drag due to lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)
C_D,i = (C_L^2)/(pi*e_oswald*AR)

Why does lift induced drag decrease with speed?

Induced drag decreases with the square of speed (for a constant lift), because at higher speed there is more air to accelerate, so it only needs to be accelerated by less.

How to Calculate Coefficient of Drag due to lift?

Coefficient of Drag due to lift calculator uses Coefficient of drag due to lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing) to calculate the Coefficient of drag due to lift, The Coefficient of Drag due to lift depends upon the lift coefficient, Oswald efficiency factor, and the aspect ratio of the wing. Coefficient of drag due to lift is denoted by C_D,i symbol.

How to calculate Coefficient of Drag due to lift using this online calculator? To use this online calculator for Coefficient of Drag due to lift, enter Lift Coefficient (C_L), Oswald Efficiency Factor (e_oswald) & Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Coefficient of Drag due to lift calculation can be explained with given input values -> 0.192577 = (1.1^2)/(pi*0.5*4).

FAQ

What is Coefficient of Drag due to lift?

The Coefficient of Drag due to lift depends upon the lift coefficient, Oswald efficiency factor, and the aspect ratio of the wing and is represented as C_D,i = (C_L^2)/(pi*e_oswald*AR) or Coefficient of drag due to lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing). The Lift Coefficient 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 Oswald efficiency factor is a correction factor that 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 & The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.

How to calculate Coefficient of Drag due to lift?

The Coefficient of Drag due to lift depends upon the lift coefficient, Oswald efficiency factor, and the aspect ratio of the wing is calculated using Coefficient of drag due to lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing). To calculate Coefficient of Drag due to lift, you need Lift Coefficient (C_L), Oswald Efficiency Factor (e_oswald) & Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for Lift Coefficient, Oswald Efficiency Factor & Aspect Ratio of a wing 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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