Coefficient of drag given drag Calculator

✖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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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: 2.93 Kilogram --> 2.93 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D = (C_L*F_D)/W₀ --> (1.1*80)/2.93

Evaluating ... ...

C_D = 30.0341296928328

STEP 3: Convert Result to Output's Unit

30.0341296928328 --> No Conversion Required

FINAL ANSWER

30.0341296928328 ≈ 30.03413 <-- Drag Coefficient

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Introduction and Governing Equations » Aerospace » Lift and Drag Polar » Coefficient of drag given drag

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

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< Lift and Drag Polar Calculators

Drag Coefficient for given zero-lift drag coefficient

LaTeX 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

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

Coefficient of Drag due to lift

LaTeX Go Coefficient of Drag due to Lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)

Parasite Drag Coefficient at zero lift

LaTeX Go Zero-Lift Drag Coefficient = Drag Coefficient-Coefficient of Drag due to Lift

Coefficient of drag given drag Formula

LaTeX Go

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, Coefficient of Drag given Drag is a dimensionless quantity that represents the resistance encountered by an object moving through a fluid, calculated by dividing the drag force by the product of the lift coefficient and gross weight. 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 -> 29.93197 = (1.1*80)/2.93.

FAQ

What is Coefficient of drag given drag?

Coefficient of Drag given Drag is a dimensionless quantity that represents the resistance encountered by an object moving through a fluid, calculated by dividing the drag force by the product of the lift coefficient and gross weight 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?

Coefficient of Drag given Drag is a dimensionless quantity that represents the resistance encountered by an object moving through a fluid, calculated by dividing the drag force by the product of the lift coefficient and gross weight 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 3 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

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