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Minimum Thrust required for given weight 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{{W body}^{2}}{P dynamic \cdot A \cdot π \cdot e \cdot AR})

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

Minimum Thrust required for given weight Example

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

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

100.1043 = (10 \cdot 20 \cdot 0.31) + (\frac{221^{2}}{10 \cdot 20 \cdot 3.1416 \cdot 0.51 \cdot 4})

100.1043N = (10Pa \cdot 20m² \cdot 0.31) + (\frac{{221N}^{2}}{10Pa \cdot 20m² \cdot 3.1416 \cdot 0.51 \cdot 4})

100.1043 = (10 \cdot 20 \cdot 0.31) + (\frac{221^{2}}{10 \cdot 20 \cdot 3.1416 \cdot 0.51 \cdot 4})

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Minimum Thrust required for given weight Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

T = (10Pa \cdot 20m² \cdot 0.31) + (\frac{{221N}^{2}}{10Pa \cdot 20m² \cdot π \cdot 0.51 \cdot 4})

Next Step Substitute values of Constants

∴

T = (10Pa \cdot 20m² \cdot 0.31) + (\frac{{221N}^{2}}{10Pa \cdot 20m² \cdot 3.1416 \cdot 0.51 \cdot 4})

Next Step Prepare to Evaluate

∴

T = (10 \cdot 20 \cdot 0.31) + (\frac{221^{2}}{10 \cdot 20 \cdot 3.1416 \cdot 0.51 \cdot 4})

Next Step Evaluate

∴

T = 100.104345958585N

LAST Step Rounding Answer

∴

T = 100.1043N

Minimum Thrust required for given weight 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

Weight of Body

Weight of Body is the force acting on the object due to gravity.

Symbol: W_body

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Weight of Body

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 weight?

Minimum Thrust required for given weight evaluator uses Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)) to evaluate the Thrust, The Minimum Thrust required for given Weight is the least amount of propulsive force needed to sustain level flight while supporting the aircraft's weight, achieving this minimum thrust typically involves optimizing the aircraft's aerodynamic configuration to reduce drag while maintaining the necessary lift to counteract the weight. Thrust is denoted by T symbol.

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

FAQs on Minimum Thrust required for given weight

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

The formula of Minimum Thrust required for given weight is expressed as Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). Here is an example- 75.70435 = (10*20*0.31)+((221^2)/(10*20*pi*0.51*4)).

How to calculate Minimum Thrust required for given weight?

With Dynamic Pressure (P_dynamic), Area (A), Zero Lift Drag Coefficient (C_D,0), Weight of Body (W_body), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR) we can find Minimum Thrust required for given weight using the formula - Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*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 weight be negative?

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

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

Minimum Thrust required for given weight 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 weight can be measured.

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: Value
: Unit

Minimum Thrust required for given weight Formula

​GoThrust for Level and Unaccelerated Flight Formula

​GoThrust of Aircraft required for Level, Unaccelerated Flight Formula

Minimum Thrust required for given weight Example

Minimum Thrust required for given weight Solution

Minimum Thrust required for given weight Formula Elements

Other Formulas to find Thrust

Other formulas in Thrust and Power Requirements category

How to Evaluate Minimum Thrust required for given weight?

FAQs on Minimum Thrust required for given weight

Variable Name

GoThrust for Level and Unaccelerated Flight Formula

GoThrust of Aircraft required for Level, Unaccelerated Flight Formula