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Zero-Lift Drag Coefficient for given Lift Coefficient Formula

GoZero-Lift Drag Coefficient given required Thrust Formula

GoZero-Lift Drag Coefficient for Minimum Power required Formula

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Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift. Check FAQs

C D,0 = (\frac{T}{P dynamic \cdot A}) - (\frac{{C L}^{2}}{π \cdot e \cdot AR})

C_D,0 - Zero Lift Drag Coefficient?T - Thrust?P_dynamic - Dynamic Pressure?A - Area?C_L - Lift Coefficient?e - Oswald Efficiency Factor?AR - Aspect Ratio of a Wing?π - Archimedes' constant?

Zero-Lift Drag Coefficient for given Lift Coefficient Example

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Here is how the Zero-Lift Drag Coefficient for given Lift Coefficient equation looks like with Values.

Here is how the Zero-Lift Drag Coefficient for given Lift Coefficient equation looks like with Units.

Here is how the Zero-Lift Drag Coefficient for given Lift Coefficient equation looks like.

0.3112 = (\frac{100}{10 \cdot 20}) - (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4})

0.3112 = (\frac{100N}{10Pa \cdot 20m²}) - (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4})

0.3112 = (\frac{100}{10 \cdot 20}) - (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4})

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Zero-Lift Drag Coefficient for given Lift Coefficient Solution

Follow our step by step solution on how to calculate Zero-Lift Drag Coefficient for given Lift Coefficient?

FIRST Step Consider the formula

C D,0 = (\frac{T}{P dynamic \cdot A}) - (\frac{{C L}^{2}}{π \cdot e \cdot AR})

Next Step Substitute values of Variables

∴

C D,0 = (\frac{100N}{10Pa \cdot 20m²}) - (\frac{{1.1}^{2}}{π \cdot 0.51 \cdot 4})

Next Step Substitute values of Constants

∴

C D,0 = (\frac{100N}{10Pa \cdot 20m²}) - (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4})

Next Step Prepare to Evaluate

∴

C D,0 = (\frac{100}{10 \cdot 20}) - (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4})

Next Step Evaluate

∴

C D,0 = 0.311198547900791

LAST Step Rounding Answer

∴

C D,0 = 0.3112

Zero-Lift Drag Coefficient for given Lift Coefficient Formula Elements

Variables

Constants

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.

Symbol: C_D,0

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Zero Lift Drag Coefficient

Thrust

The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

Symbol: T

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Thrust

Dynamic Pressure

Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.

Symbol: P_dynamic

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Dynamic Pressure

Area

The Area is the amount of two-dimensional space taken up by an object.

Symbol: A

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Area

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.

Symbol: C_L

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient

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.

Symbol: e

Measurement: NAUnit: Unitless

Note: Value should be less than 1.

Formulas to find Oswald Efficiency Factor

Aspect Ratio of a Wing

The Aspect Ratio of a Wing is defined as the ratio of its span to its mean chord.

Symbol: AR

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Aspect Ratio of a Wing

Archimedes' constant

Archimedes' constant is a mathematical constant that represents the ratio of the circumference of a circle to its diameter.

Symbol: π

Value: 3.14159265358979323846264338327950288

Other Formulas to find Zero Lift Drag Coefficient

Go Zero-Lift Drag Coefficient given required Thrust

C D,0 = (\frac{T}{P dynamic \cdot S}) - C D,i

Go Zero-Lift Drag Coefficient for Minimum Power required

C D,0 = \frac{C D,i}{3}

Other formulas in Lift and Drag Requirements category

Go Drag for Level and Unaccelerated Flight

F D = T \cdot \cos (σ T)

Go Lift for Unaccelerated Flight

F L = W body - T \cdot \sin (σ T)

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

Zero-Lift Drag Coefficient for given Lift Coefficient evaluator uses Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)) to evaluate 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 evaluate Zero-Lift Drag Coefficient for given Lift Coefficient using this online evaluator? To use this online evaluator 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.

FAQs on Zero-Lift Drag Coefficient for given Lift Coefficient

What is the formula to find Zero-Lift Drag Coefficient for given Lift Coefficient?

The formula of Zero-Lift Drag Coefficient for given Lift Coefficient is expressed as Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). Here is an example- 0.311199 = (100/(10*20))-((1.1^2)/(pi*0.51*4)).

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

With Thrust (T), Dynamic Pressure (P_dynamic), Area (A), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR) we can find Zero-Lift Drag Coefficient for given Lift Coefficient using the formula - Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). This formula also uses Archimedes' constant .

What are the other ways to Calculate Zero Lift Drag Coefficient?

Here are the different ways to Calculate Zero Lift Drag Coefficient-

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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Zero-Lift Drag Coefficient for given Lift Coefficient Formula

​GoZero-Lift Drag Coefficient given required Thrust Formula

​GoZero-Lift Drag Coefficient for Minimum Power required Formula

Zero-Lift Drag Coefficient for given Lift Coefficient Example

Zero-Lift Drag Coefficient for given Lift Coefficient Solution

Zero-Lift Drag Coefficient for given Lift Coefficient Formula Elements

Other Formulas to find Zero Lift Drag Coefficient

Other formulas in Lift and Drag Requirements category

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

FAQs on Zero-Lift Drag Coefficient for given Lift Coefficient

Variable Name

GoZero-Lift Drag Coefficient given required Thrust Formula

GoZero-Lift Drag Coefficient for Minimum Power required Formula