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Minimum Thrust required for given Lift Coefficient Formula

GoThrust for Level and Unaccelerated Flight Formula

GoThrust of Aircraft required for Level, Unaccelerated Flight Formula

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

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

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

Minimum Thrust required for given Lift Coefficient Example

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Here is how the Minimum Thrust required for given Lift Coefficient equation looks like with Units.

Here is how the Minimum Thrust required for given Lift Coefficient equation looks like.

99.7603 = 10 \cdot 20 \cdot (0.31 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}))

99.7603N = 10Pa \cdot 20m² \cdot (0.31 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}))

99.7603 = 10 \cdot 20 \cdot (0.31 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}))

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Minimum Thrust required for given Lift Coefficient Solution

Follow our step by step solution on how to calculate Minimum Thrust required for given Lift Coefficient?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

T = 10Pa \cdot 20m² \cdot (0.31 + (\frac{{1.1}^{2}}{π \cdot 0.51 \cdot 4}))

Next Step Substitute values of Constants

∴

T = 10Pa \cdot 20m² \cdot (0.31 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}))

Next Step Prepare to Evaluate

∴

T = 10 \cdot 20 \cdot (0.31 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.51 \cdot 4}))

Next Step Evaluate

∴

T = 99.7602904198419N

LAST Step Rounding Answer

∴

T = 99.7603N

Minimum Thrust required for given Lift Coefficient Formula Elements

Variables

Constants

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

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

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 Thrust

Go Thrust for Level and Unaccelerated Flight

T = \frac{F D}{\cos (σ T)}

Go Thrust of Aircraft required for Level, Unaccelerated Flight

T = P dynamic \cdot A \cdot C D

Other formulas in Thrust and Power Requirements category

Go Thrust Angle for Unaccelerated Level Flight for given Drag

σ T = a \cos (\frac{F D}{T})

Go Weight of Aircraft in Level, Unaccelerated Flight

W body = F L + (T \cdot \sin (σ T))

How to Evaluate Minimum Thrust required for given Lift Coefficient?

Minimum Thrust required for given Lift Coefficient evaluator uses Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))) to evaluate the Thrust, The Minimum Thrust required for given Lift Coefficient represents the least amount of propulsive force necessary to maintain level flight while generating a specified lift coefficient, in level flight, where lift equals weight and thrust equals drag, achieving the minimum thrust required involves minimizing the drag coefficient. Thrust is denoted by T symbol.

How to evaluate Minimum Thrust required for given Lift Coefficient using this online evaluator? To use this online evaluator for Minimum Thrust required for given Lift Coefficient, enter Dynamic Pressure (P_dynamic), Area (A), Zero Lift Drag Coefficient (C_D,0), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR) and hit the calculate button.

FAQs on Minimum Thrust required for given Lift Coefficient

What is the formula to find Minimum Thrust required for given Lift Coefficient?

The formula of Minimum Thrust required for given Lift Coefficient is expressed as Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))). Here is an example- 75.36029 = 10*20*(0.31+((1.1^2)/(pi*0.51*4))).

How to calculate Minimum Thrust required for given Lift Coefficient?

With Dynamic Pressure (P_dynamic), Area (A), Zero Lift Drag Coefficient (C_D,0), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR) we can find Minimum Thrust required for given Lift Coefficient using the formula - Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((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 Thrust?

Here are the different ways to Calculate Thrust-

Thrust=Drag Force/(cos(Thrust Angle))
Thrust=Dynamic Pressure*Area*Drag Coefficient
Thrust=Drag Coefficient*Weight of Body/Lift Coefficient

Can the Minimum Thrust required for given Lift Coefficient be negative?

No, the Minimum Thrust required for given Lift Coefficient, measured in Force cannot be negative.

Which unit is used to measure Minimum Thrust required for given Lift Coefficient?

Minimum Thrust required for given Lift Coefficient is usually measured using the Newton[N] for Force. Exanewton[N], Meganewton[N], Kilonewton[N] are the few other units in which Minimum Thrust required for given Lift Coefficient can be measured.

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: Value
: Unit

Minimum Thrust required for given Lift Coefficient Formula

​GoThrust for Level and Unaccelerated Flight Formula

​GoThrust of Aircraft required for Level, Unaccelerated Flight Formula

Minimum Thrust required for given Lift Coefficient Example

Minimum Thrust required for given Lift Coefficient Solution

Minimum Thrust required for given Lift Coefficient Formula Elements

Other Formulas to find Thrust

Other formulas in Thrust and Power Requirements category

How to Evaluate Minimum Thrust required for given Lift Coefficient?

FAQs on Minimum Thrust required for given Lift Coefficient

Variable Name

GoThrust for Level and Unaccelerated Flight Formula

GoThrust of Aircraft required for Level, Unaccelerated Flight Formula