Induced Drag Coefficient Calculator

↳

⤿

Two-Dimensional Incompressible Flow

Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

⤿

Flow over Airfoils and Wings

Elementary Flows

Flow and Lift Distribution

⤿

✖Induced Drag is caused by that element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it.ⓘ Induced Drag [D_i]			+10% -10%
✖Free Stream Dynamic Pressure is the kinetic energy per unit volume of fluid at some distance from the body where the density and velocity are freestream values.ⓘ Free Stream Dynamic Pressure [q_∞]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%

✖The Induced Drag Coefficient is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.ⓘ Induced Drag Coefficient [C_D,i]

⎘ Copy

👎

Formula

✖

Induced Drag Coefficient

Formula

`"C"_{"D,i"} = "D"_{"i"}/("q"_{"∞"}*"S")`

Example

`"0.039376"="101N"/("450Pa"*"5.7m²")`

Calculator

LaTeX

Reset

👍

Download Flow over Airfoils and Wings Formulas PDF

Induced Drag Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Drag Coefficient = Induced Drag/(Free Stream Dynamic Pressure*Reference Area)
C_D,i = D_i/(q_∞*S)
This formula uses 4 Variables

Variables Used

Induced Drag Coefficient - The Induced Drag Coefficient is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.
Induced Drag - (Measured in Newton) - Induced Drag is caused by that element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it.
Free Stream Dynamic Pressure - (Measured in Pascal) - Free Stream Dynamic Pressure is the kinetic energy per unit volume of fluid at some distance from the body where the density and velocity are freestream values.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.

STEP 1: Convert Input(s) to Base Unit

Induced Drag: 101 Newton --> 101 Newton No Conversion Required
Free Stream Dynamic Pressure: 450 Pascal --> 450 Pascal No Conversion Required
Reference Area: 5.7 Square Meter --> 5.7 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,i = D_i/(q_∞*S) --> 101/(450*5.7)

Evaluating ... ...

C_D,i = 0.0393762183235867

STEP 3: Convert Result to Output's Unit

0.0393762183235867 --> No Conversion Required

FINAL ANSWER

0.0393762183235867 ≈ 0.039376 <-- Induced Drag Coefficient

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aerodynamics » Two-Dimensional Incompressible Flow » Flow over Airfoils and Wings » Induced Drag » Induced Drag Coefficient

Credits

Created by Ravi Khiyani

Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore

Ravi Khiyani has created this Calculator and 200+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< 7 Induced Drag Calculators

Profile Drag Coefficient

Go Profile Drag Coefficient = (Skin Friction Drag Force+Pressure Drag Force)/(Free Stream Dynamic Pressure*Reference Area)

Induced Drag Coefficient

Go Induced Drag Coefficient = Induced Drag/(Free Stream Dynamic Pressure*Reference Area)

Velocity Induced at Point by Semi-infinite Straight Vortex Filament

Go Induced Velocity = Vortex Strength/(4*pi*Perpendicular Distance to Vortex)

Velocity Induced at Point by Infinite Straight Vortex Filament

Go Induced Velocity = Vortex Strength/(2*pi*Perpendicular Distance to Vortex)

Induced Drag Coefficient given Total Drag Coefficient

Go Induced Drag Coefficient = Total Drag Coefficient-Profile Drag Coefficient

Profile Drag Coefficient given Total Drag Coefficient

Go Profile Drag Coefficient = Total Drag Coefficient-Induced Drag Coefficient

Total Drag Coefficient for Subsonic Finite Wing

Go Total Drag Coefficient = Profile Drag Coefficient+Induced Drag Coefficient

Induced Drag Coefficient Formula

Induced Drag Coefficient = Induced Drag/(Free Stream Dynamic Pressure*Reference Area)
C_D,i = D_i/(q_∞*S)

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?

Induced Drag Coefficient calculator uses Induced Drag Coefficient = Induced Drag/(Free Stream Dynamic Pressure*Reference Area) to calculate the Induced Drag Coefficient, The Induced Drag Coefficient formula calculates the coefficient for the 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 results from lift generation by an aerodynamic body, creating vortices at wingtips that induce a downwash, tilting airflow downward and producing drag-opposing motion. Induced Drag Coefficient is denoted by C_D,i symbol.

How to calculate Induced Drag Coefficient using this online calculator? To use this online calculator for Induced Drag Coefficient, enter Induced Drag (D_i), Free Stream Dynamic Pressure (q_∞) & Reference Area (S) and hit the calculate button. Here is how the Induced Drag Coefficient calculation can be explained with given input values -> 0.044182 = 101/(450*5.7).

FAQ

What is Induced Drag Coefficient?

The Induced Drag Coefficient formula calculates the coefficient for the 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 results from lift generation by an aerodynamic body, creating vortices at wingtips that induce a downwash, tilting airflow downward and producing drag-opposing motion and is represented as C_D,i = D_i/(q_∞*S) or Induced Drag Coefficient = Induced Drag/(Free Stream Dynamic Pressure*Reference Area). Induced Drag is caused by that element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it, Free Stream Dynamic Pressure is the kinetic energy per unit volume of fluid at some distance from the body where the density and velocity are freestream values & The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.

How to calculate Induced Drag Coefficient?

The Induced Drag Coefficient formula calculates the coefficient for the 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 results from lift generation by an aerodynamic body, creating vortices at wingtips that induce a downwash, tilting airflow downward and producing drag-opposing motion is calculated using Induced Drag Coefficient = Induced Drag/(Free Stream Dynamic Pressure*Reference Area). To calculate Induced Drag Coefficient, you need Induced Drag (D_i), Free Stream Dynamic Pressure (q_∞) & Reference Area (S). With our tool, you need to enter the respective value for Induced Drag, Free Stream Dynamic Pressure & Reference Area 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?

In this formula, Induced Drag Coefficient uses Induced Drag, Free Stream Dynamic Pressure & Reference Area. We can use 1 other way(s) to calculate the same, which is/are as follows -

Induced Drag Coefficient = Total Drag Coefficient-Profile Drag Coefficient

Home

FREE PDFs

🔍 Search