Drag Coefficient for given zero-lift drag coefficient Calculator

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✖The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitude.ⓘ Zero-lift drag coefficient [C_D,0]			+10% -10%
✖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%

✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient for given zero-lift drag coefficient [C_D]

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Formula

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Drag Coefficient for given zero-lift drag coefficient

Formula

`"C"_{"D"} = "C"_{"D,0"}+(("C"_{"L"}^2)/(pi*"e"_{"oswald"}*"AR"))`

Example

`"0.208677"="0.0161"+((("1.1")^2)/(pi*"0.5"*"4"))`

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Drag Coefficient for given zero-lift drag coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Drag Coefficient = Zero-lift drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
C_D = C_D,0+((C_L^2)/(pi*e_oswald*AR))
This formula uses 1 Constants, 5 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
Zero-lift drag coefficient - The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitude.
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

Zero-lift drag coefficient: 0.0161 --> No Conversion Required
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 = C_D,0+((C_L^2)/(pi*e_oswald*AR)) --> 0.0161+((1.1^2)/(pi*0.5*4))

Evaluating ... ...

C_D = 0.208677481141193

STEP 3: Convert Result to Output's Unit

0.208677481141193 --> No Conversion Required

FINAL ANSWER

0.208677481141193 ≈ 0.208677 <-- Drag Coefficient

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Introduction and Governing Equations » Lift and Drag Polar » Drag Coefficient for given zero-lift drag coefficient

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Created by Vinay Mishra

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

Drag Coefficient for given zero-lift drag coefficient Formula

Drag Coefficient = Zero-lift drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
C_D = C_D,0+((C_L^2)/(pi*e_oswald*AR))

Can a drag coefficient be negative?

Drag coefficient cannot be negative in steady flow and a negative value of drag coefficient in steady flow indicates a computational error.

How to Calculate Drag Coefficient for given zero-lift drag coefficient?

Drag Coefficient for given zero-lift drag coefficient calculator uses Drag Coefficient = Zero-lift drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)) to calculate the Drag Coefficient, The Drag Coefficient for given zero-lift drag coefficient is the drag coefficient of the complete airplane as a function of the total lift coefficient and the zero-lift drag coefficient. Drag Coefficient is denoted by C_D symbol.

How to calculate Drag Coefficient for given zero-lift drag coefficient using this online calculator? To use this online calculator for Drag Coefficient for given zero-lift drag coefficient, enter Zero-lift drag coefficient (C_D,0), Lift Coefficient (C_L), Oswald Efficiency Factor (e_oswald) & Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Drag Coefficient for given zero-lift drag coefficient calculation can be explained with given input values -> 0.208677 = 0.0161+((1.1^2)/(pi*0.5*4)).

FAQ

What is Drag Coefficient for given zero-lift drag coefficient?

The Drag Coefficient for given zero-lift drag coefficient is the drag coefficient of the complete airplane as a function of the total lift coefficient and the zero-lift drag coefficient and is represented as C_D = C_D,0+((C_L^2)/(pi*e_oswald*AR)) or Drag Coefficient = Zero-lift drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)). The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitude, 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 Drag Coefficient for given zero-lift drag coefficient?

The Drag Coefficient for given zero-lift drag coefficient is the drag coefficient of the complete airplane as a function of the total lift coefficient and the zero-lift drag coefficient is calculated using Drag Coefficient = Zero-lift drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)). To calculate Drag Coefficient for given zero-lift drag coefficient, you need Zero-lift drag coefficient (C_D,0), 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 Zero-lift drag coefficient, 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.

How many ways are there to calculate Drag Coefficient?

In this formula, Drag Coefficient uses Zero-lift drag coefficient, Lift Coefficient, Oswald Efficiency Factor & Aspect Ratio of a wing. We can use 4 other way(s) to calculate the same, which is/are as follows -

Drag Coefficient = Parasite Drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
Drag Coefficient = Drag Force/Dynamic Pressure
Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight
Drag Coefficient = Lift Coefficient*Drag Force/Lift Force

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