Parasite Drag Coefficient at zero lift Calculator

⤿

Introduction and Governing Equations

Aircraft Design

Aircraft Performance

Static Stability and Control

⤿

Lift and Drag Polar

Aircraft Dynamics Nomenclature

Atmosphere and Gas Properties

Preliminary Aerodynamics

✖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 [C_D]			+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]			+10% -10%

✖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.ⓘ Parasite Drag Coefficient at zero lift [C_D,0]

⎘ Copy

👎

Formula

✖

Parasite Drag Coefficient at zero lift

Formula

`"C"_{"D,0"} = "C"_{"D"}-"C"_{"D,i"}`

Example

`"29.2"="30"-"0.8"`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF PDF Image

Parasite Drag Coefficient at zero lift Solution

STEP 0: Pre-Calculation Summary

Formula Used

Zero-lift drag coefficient = Drag Coefficient-Coefficient of drag due to lift
C_D,0 = C_D-C_D,i
This formula uses 3 Variables

Variables Used

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.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Drag Coefficient: 30 --> No Conversion Required
Coefficient of drag due to lift: 0.8 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,0 = C_D-C_D,i --> 30-0.8

Evaluating ... ...

C_D,0 = 29.2

STEP 3: Convert Result to Output's Unit

29.2 --> No Conversion Required

FINAL ANSWER

29.2 <-- Zero-lift drag coefficient

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Introduction and Governing Equations » Lift and Drag Polar » Parasite Drag Coefficient at zero lift

Credits

Created by Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Chilvera Bhanu Teja

Institute of Aeronautical Engineering (IARE), Hyderabad

Chilvera Bhanu Teja has verified this Calculator and 200+ more calculators!

< 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

Parasite Drag Coefficient at zero lift Formula

Zero-lift drag coefficient = Drag Coefficient-Coefficient of drag due to lift
C_D,0 = C_D-C_D,i

How do you stop a parasitic drag?

There are two ways to decrease friction drag: the first is to shape the moving body so that laminar flow is possible. The second method is to increase the length and decrease the cross-section of the moving object as much as practicable.

How to Calculate Parasite Drag Coefficient at zero lift?

Parasite Drag Coefficient at zero lift calculator uses Zero-lift drag coefficient = Drag Coefficient-Coefficient of drag due to lift to calculate the Zero-lift drag coefficient, The Parasite Drag Coefficient at zero lift is approximately equal to the drag of a flat square disk with the same area which is held perpendicular to the direction of flight. Zero-lift drag coefficient is denoted by C_D,0 symbol.

How to calculate Parasite Drag Coefficient at zero lift using this online calculator? To use this online calculator for Parasite Drag Coefficient at zero lift, enter Drag Coefficient (C_D) & Coefficient of drag due to lift (C_D,i) and hit the calculate button. Here is how the Parasite Drag Coefficient at zero lift calculation can be explained with given input values -> 29.2 = 30-0.8.

FAQ

What is Parasite Drag Coefficient at zero lift?

The Parasite Drag Coefficient at zero lift is approximately equal to the drag of a flat square disk with the same area which is held perpendicular to the direction of flight and is represented as C_D,0 = C_D-C_D,i or Zero-lift drag coefficient = Drag Coefficient-Coefficient of drag due to lift. 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 & 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.

How to calculate Parasite Drag Coefficient at zero lift?

The Parasite Drag Coefficient at zero lift is approximately equal to the drag of a flat square disk with the same area which is held perpendicular to the direction of flight is calculated using Zero-lift drag coefficient = Drag Coefficient-Coefficient of drag due to lift. To calculate Parasite Drag Coefficient at zero lift, you need Drag Coefficient (C_D) & Coefficient of drag due to lift (C_D,i). With our tool, you need to enter the respective value for Drag Coefficient & Coefficient of drag due to lift and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search