Zero-Lift Drag Coefficient for given Lift Coefficient Calculator

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust [T]			+10% -10%
✖Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.ⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The Area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+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]			+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%

✖Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.ⓘ Zero-Lift Drag Coefficient for given Lift Coefficient [C_D,0]

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Zero-Lift Drag Coefficient for given Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))
C_D,0 = (T/(P_dynamic*A))-((C_L^2)/(pi*e*AR))
This formula uses 1 Constants, 7 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Zero Lift Drag Coefficient - Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.
Thrust - (Measured in Newton) - The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.
Area - (Measured in Square Meter) - The Area is the amount of two-dimensional space taken up by an object.
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

Thrust: 100 Newton --> 100 Newton No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Area: 20 Square Meter --> 20 Square Meter No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required
Oswald Efficiency Factor: 0.51 --> No Conversion Required
Aspect Ratio of a Wing: 4 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,0 = (T/(P_dynamic*A))-((C_L^2)/(pi*e*AR)) --> (100/(10*20))-((1.1^2)/(pi*0.51*4))

Evaluating ... ...

C_D,0 = 0.311198547900791

STEP 3: Convert Result to Output's Unit

0.311198547900791 --> No Conversion Required

FINAL ANSWER

0.311198547900791 ≈ 0.311199 <-- Zero Lift Drag Coefficient

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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< Lift and Drag Requirements Calculators

Lift for Unaccelerated Flight

LaTeX Go Lift Force = Weight of Body-Thrust*sin(Thrust Angle)

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Drag Force = Dynamic Pressure*Area*Drag Coefficient

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Lift Force = Dynamic Pressure*Area*Lift Coefficient

Drag for Level and Unaccelerated Flight

LaTeX Go Drag Force = Thrust*cos(Thrust Angle)

Zero-Lift Drag Coefficient for given Lift Coefficient Formula

LaTeX Go

Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))
C_D,0 = (T/(P_dynamic*A))-((C_L^2)/(pi*e*AR))

How is the reference area chosen?

The reference area is arbitrary in principle. It is chosen as the area that is characteristic of the object considered. As an example, in aircraft aerodynamics, typically the planform area of the wing is chosen as the reference area for both lift and drag coefficients of the wing.

How to Calculate Zero-Lift Drag Coefficient for given Lift Coefficient?

Zero-Lift Drag Coefficient for given Lift Coefficient calculator uses Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)) to calculate the Zero Lift Drag Coefficient, The Zero-Lift Drag Coefficient for given Lift Coefficient is a parameter used in aerodynamics to quantify the drag on an aircraft when it is producing zero lift, it represents the drag caused by factors such as the shape of the aircraft, skin friction, and other non-lift-producing elements. Zero Lift Drag Coefficient is denoted by C_D,0 symbol.

How to calculate Zero-Lift Drag Coefficient for given Lift Coefficient using this online calculator? To use this online calculator for Zero-Lift Drag Coefficient for given Lift Coefficient, enter Thrust (T), Dynamic Pressure (P_dynamic), Area (A), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR) and hit the calculate button. Here is how the Zero-Lift Drag Coefficient for given Lift Coefficient calculation can be explained with given input values -> 0.311199 = (100/(10*20))-((1.1^2)/(pi*0.51*4)).

FAQ

What is Zero-Lift Drag Coefficient for given Lift Coefficient?

The Zero-Lift Drag Coefficient for given Lift Coefficient is a parameter used in aerodynamics to quantify the drag on an aircraft when it is producing zero lift, it represents the drag caused by factors such as the shape of the aircraft, skin friction, and other non-lift-producing elements and is represented as C_D,0 = (T/(P_dynamic*A))-((C_L^2)/(pi*e*AR)) or Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air, Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion, The Area is the amount of two-dimensional space taken up by an object, 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 Zero-Lift Drag Coefficient for given Lift Coefficient?

The Zero-Lift Drag Coefficient for given Lift Coefficient is a parameter used in aerodynamics to quantify the drag on an aircraft when it is producing zero lift, it represents the drag caused by factors such as the shape of the aircraft, skin friction, and other non-lift-producing elements is calculated using Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). To calculate Zero-Lift Drag Coefficient for given Lift Coefficient, you need Thrust (T), Dynamic Pressure (P_dynamic), Area (A), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR). With our tool, you need to enter the respective value for Thrust, Dynamic Pressure, Area, 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 Zero Lift Drag Coefficient?

In this formula, Zero Lift Drag Coefficient uses Thrust, Dynamic Pressure, Area, Lift Coefficient, Oswald Efficiency Factor & Aspect Ratio of a Wing. We can use 2 other way(s) to calculate the same, which is/are as follows -

Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift
Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3

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