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Nozzle Thrust Coefficient Formula

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The thrust coefficient is a dimensionless parameter used in fluid dynamics and aerodynamics to characterize the efficiency of a propulsion system. Check FAQs

C F = \frac{F}{A t \cdot P 1}

C_F - Thrust Coefficient?F - Rocket Thrust?A_t - Nozzle Throat Area?P₁ - Inlet Nozzle Pressure?

Nozzle Thrust Coefficient Example

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Here is how the Nozzle Thrust Coefficient equation looks like with Values.

Here is how the Nozzle Thrust Coefficient equation looks like with Units.

Here is how the Nozzle Thrust Coefficient equation looks like.

198.9313 = \frac{154569.6}{0.21 \cdot 0.0037}

198.9313 = \frac{154569.6N}{0.21m² \cdot 0.0037MPa}

198.9313 = \frac{154569.6}{0.21 \cdot 0.0037}

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Nozzle Thrust Coefficient Solution

Follow our step by step solution on how to calculate Nozzle Thrust Coefficient?

FIRST Step Consider the formula

C F = \frac{F}{A t \cdot P 1}

Next Step Substitute values of Variables

∴

C F = \frac{154569.6N}{0.21m² \cdot 0.0037MPa}

Next Step Convert Units

∴

C F = \frac{154569.6N}{0.21m² \cdot 3700Pa}

Next Step Prepare to Evaluate

∴

C F = \frac{154569.6}{0.21 \cdot 3700}

Next Step Evaluate

∴

C F = 198.931274131274

LAST Step Rounding Answer

∴

C F = 198.9313

Nozzle Thrust Coefficient Formula Elements

Variables

Thrust Coefficient

The thrust coefficient is a dimensionless parameter used in fluid dynamics and aerodynamics to characterize the efficiency of a propulsion system.

Symbol: C_F

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Thrust Coefficient

Rocket Thrust

Rocket Thrust determines the acceleration and performance capabilities of rocket.

Symbol: F

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Rocket Thrust

Nozzle Throat Area

The nozzle throat area refers to the cross-sectional area of the narrowest part of a propulsion nozzle, known as the throat.

Symbol: A_t

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Nozzle Throat Area

Inlet Nozzle Pressure

Inlet Nozzle Pressure represents the pressure of the incoming air or propellant before it enters the combustion chamber or the turbine section.

Symbol: P₁

Measurement: PressureUnit: MPa

Note: Value can be positive or negative.

Formulas to find Inlet Nozzle Pressure

Other formulas in Nozzles category

Go Propulsion Efficiency

η prop = \frac{2 \cdot (\frac{v 0}{v 9})}{1 + {(\frac{v 0}{v 9})}^{2}}

Go Specific Volume at Throat

V t = V 1 \cdot {(\frac{γ + 1}{2})}^{\frac{1}{γ - 1}}

Go Specific Temperature at Throat

T t = \frac{2 \cdot T 1}{γ + 1}

Go Characteristics Velocity

C ✸ = \sqrt{(\frac{[R] \cdot T 1}{γ}) \cdot {(\frac{γ + 1}{2})}^{\frac{γ + 1}{γ - 1}}}

How to Evaluate Nozzle Thrust Coefficient?

Nozzle Thrust Coefficient evaluator uses Thrust Coefficient = Rocket Thrust/(Nozzle Throat Area*Inlet Nozzle Pressure) to evaluate the Thrust Coefficient, The nozzle thrust coefficient provides insights into how effectively the engine is converting its energy source (such as fuel or propellant) into thrust, it's a crucial parameter for assessing the performance and efficiency of propulsion systems. Thrust Coefficient is denoted by C_F symbol.

How to evaluate Nozzle Thrust Coefficient using this online evaluator? To use this online evaluator for Nozzle Thrust Coefficient, enter Rocket Thrust (F), Nozzle Throat Area (A_t) & Inlet Nozzle Pressure (P₁) and hit the calculate button.

FAQs on Nozzle Thrust Coefficient

What is the formula to find Nozzle Thrust Coefficient?

The formula of Nozzle Thrust Coefficient is expressed as Thrust Coefficient = Rocket Thrust/(Nozzle Throat Area*Inlet Nozzle Pressure). Here is an example- 198.9313 = 154569.6/(0.21*3700).

How to calculate Nozzle Thrust Coefficient?

With Rocket Thrust (F), Nozzle Throat Area (A_t) & Inlet Nozzle Pressure (P₁) we can find Nozzle Thrust Coefficient using the formula - Thrust Coefficient = Rocket Thrust/(Nozzle Throat Area*Inlet Nozzle Pressure).

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