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Zero-lift drag coefficient at minimum required thrust Formula

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The Zero-Lift Drag Coefficient at Minimum Thrust represents the drag coefficient of an aircraft when it is producing zero lift and operating at the minimum thrust required for level flight. Check FAQs

C D0,min = \frac{{C L}^{2}}{π \cdot e \cdot AR}

C_D0,min - Zero-Lift Drag Coefficient at Minimum Thrust?C_L - Lift Coefficient?e - Oswald Efficiency Factor?AR - Aspect Ratio of a Wing?π - Archimedes' constant?

Zero-lift drag coefficient at minimum required thrust Example

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Here is how the Zero-lift drag coefficient at minimum required thrust equation looks like with Values.

Here is how the Zero-lift drag coefficient at minimum required thrust equation looks like with Units.

Here is how the Zero-lift drag coefficient at minimum required thrust equation looks like.

0.1888 = \frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}

0.1888 = \frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}

0.1888 = \frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}

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Zero-lift drag coefficient at minimum required thrust Solution

Follow our step by step solution on how to calculate Zero-lift drag coefficient at minimum required thrust?

FIRST Step Consider the formula

C D0,min = \frac{{C L}^{2}}{π \cdot e \cdot AR}

Next Step Substitute values of Variables

∴

C D0,min = \frac{{1.1}^{2}}{π \cdot 0.51 \cdot 4}

Next Step Substitute values of Constants

∴

C D0,min = \frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}

Next Step Prepare to Evaluate

∴

C D0,min = \frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}

Next Step Evaluate

∴

C D0,min = 0.188801452099209

LAST Step Rounding Answer

∴

C D0,min = 0.1888

Zero-lift drag coefficient at minimum required thrust Formula Elements

Variables

Constants

Zero-Lift Drag Coefficient at Minimum Thrust

The Zero-Lift Drag Coefficient at Minimum Thrust represents the drag coefficient of an aircraft when it is producing zero lift and operating at the minimum thrust required for level flight.

Symbol: C_D0,min

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Zero-Lift Drag Coefficient at Minimum Thrust

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 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)

Go Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

F D = P dynamic \cdot A \cdot C D

Go Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

F L = P dynamic \cdot A \cdot C L

How to Evaluate Zero-lift drag coefficient at minimum required thrust?

Zero-lift drag coefficient at minimum required thrust evaluator uses Zero-Lift Drag Coefficient at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing) to evaluate the Zero-Lift Drag Coefficient at Minimum Thrust, The Zero-lift drag coefficient at minimum required thrust refers to a specific aerodynamic parameter of an aircraft, it represents the drag force produced by an aircraft when it generates zero lift and is typically measured at a specific condition such as zero angle of attack, the minimum required thrust refers to the lowest amount of engine thrust necessary to maintain level flight at a certain speed. Zero-Lift Drag Coefficient at Minimum Thrust is denoted by C_D0,min symbol.

How to evaluate Zero-lift drag coefficient at minimum required thrust using this online evaluator? To use this online evaluator for Zero-lift drag coefficient at minimum required thrust, enter 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 at minimum required thrust

What is the formula to find Zero-lift drag coefficient at minimum required thrust?

The formula of Zero-lift drag coefficient at minimum required thrust is expressed as Zero-Lift Drag Coefficient at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing). Here is an example- 0.188801 = (1.1^2)/(pi*0.51*4).

How to calculate Zero-lift drag coefficient at minimum required thrust?

With Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR) we can find Zero-lift drag coefficient at minimum required thrust using the formula - Zero-Lift Drag Coefficient at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing). This formula also uses Archimedes' constant .

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Zero-lift drag coefficient at minimum required thrust Formula

Zero-lift drag coefficient at minimum required thrust Example

Zero-lift drag coefficient at minimum required thrust Solution

Zero-lift drag coefficient at minimum required thrust Formula Elements

Other formulas in Lift and Drag Requirements category

How to Evaluate Zero-lift drag coefficient at minimum required thrust?

FAQs on Zero-lift drag coefficient at minimum required thrust

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