Coefficient of drag given drag Calculator

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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%
✖Drag Force is the resisting force experienced by an object moving through a fluid ,such as air.ⓘ Drag Force [F_D]			+10% -10%
✖The Gross Weight of the airplane is the weight with full fuel and payload.ⓘ Gross Weight [W₀]			+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.ⓘ Coefficient of drag given drag [C_D]

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Formula

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Coefficient of drag given drag

Formula

`"C"_{"D"} = ("C"_{"L"}*"F"_{"D"})/"W"_{"0"}`

Example

`"0.0176"=("1.1"*"80N")/"5000kg"`

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Coefficient of drag given drag Solution

STEP 0: Pre-Calculation Summary

Formula Used

Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight
C_D = (C_L*F_D)/W₀
This formula uses 4 Variables

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.
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.
Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid ,such as air.
Gross Weight - (Measured in Kilogram) - The Gross Weight of the airplane is the weight with full fuel and payload.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient: 1.1 --> No Conversion Required
Drag Force: 80 Newton --> 80 Newton No Conversion Required
Gross Weight: 5000 Kilogram --> 5000 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D = (C_L*F_D)/W₀ --> (1.1*80)/5000

Evaluating ... ...

C_D = 0.0176

STEP 3: Convert Result to Output's Unit

0.0176 --> No Conversion Required

FINAL ANSWER

0.0176 <-- Drag Coefficient

(Calculation completed in 00.004 seconds)

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National Institute of Technology, Hamirpur (NITH), Himachal Pradesh

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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 given drag Formula

Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight
C_D = (C_L*F_D)/W₀

What is drag coefficient?

In fluid dynamics, the 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. It is used in the drag equation in which a lower drag coefficient indicates the object will have less aerodynamic or hydrodynamic drag.

How to Calculate Coefficient of drag given drag?

Coefficient of drag given drag calculator uses Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight to calculate the Drag Coefficient, The Coefficient of drag given drag formula is defined as drag experianced by the aircraft during its flight by the air considering gross weight, drag force and generated lift. Drag Coefficient is denoted by C_D symbol.

How to calculate Coefficient of drag given drag using this online calculator? To use this online calculator for Coefficient of drag given drag, enter Lift Coefficient (C_L), Drag Force (F_D) & Gross Weight (W₀) and hit the calculate button. Here is how the Coefficient of drag given drag calculation can be explained with given input values -> 0.0176 = (1.1*80)/5000.

FAQ

What is Coefficient of drag given drag?

The Coefficient of drag given drag formula is defined as drag experianced by the aircraft during its flight by the air considering gross weight, drag force and generated lift and is represented as C_D = (C_L*F_D)/W₀ or Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight. 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, Drag Force is the resisting force experienced by an object moving through a fluid ,such as air & The Gross Weight of the airplane is the weight with full fuel and payload.

How to calculate Coefficient of drag given drag?

The Coefficient of drag given drag formula is defined as drag experianced by the aircraft during its flight by the air considering gross weight, drag force and generated lift is calculated using Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight. To calculate Coefficient of drag given drag, you need Lift Coefficient (C_L), Drag Force (F_D) & Gross Weight (W₀). With our tool, you need to enter the respective value for Lift Coefficient, Drag Force & Gross Weight 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 Lift Coefficient, Drag Force & Gross Weight. 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 = Zero-lift 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/Lift Force

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