Nozzle Thrust Coefficient Calculator

✖Rocket Thrust determines the acceleration and performance capabilities of rocket.ⓘ Rocket Thrust [F]			+10% -10%
✖The nozzle throat area refers to the cross-sectional area of the narrowest part of a propulsion nozzle, known as the throat.ⓘ Nozzle Throat Area [A_t]			+10% -10%
✖Inlet Nozzle Pressure represents the pressure of the incoming air or propellant before it enters the combustion chamber or the turbine section.ⓘ Inlet Nozzle Pressure [P₁]			+10% -10%

✖The thrust coefficient is a dimensionless parameter used in fluid dynamics and aerodynamics to characterize the efficiency of a propulsion system.ⓘ Nozzle Thrust Coefficient [C_F]

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Nozzle Thrust Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Thrust Coefficient = Rocket Thrust/(Nozzle Throat Area*Inlet Nozzle Pressure)
C_F = F/(A_t*P₁)
This formula uses 4 Variables

Variables Used

Thrust Coefficient - The thrust coefficient is a dimensionless parameter used in fluid dynamics and aerodynamics to characterize the efficiency of a propulsion system.
Rocket Thrust - (Measured in Newton) - Rocket Thrust determines the acceleration and performance capabilities of rocket.
Nozzle Throat Area - (Measured in Square Meter) - The nozzle throat area refers to the cross-sectional area of the narrowest part of a propulsion nozzle, known as the throat.
Inlet Nozzle Pressure - (Measured in Pascal) - Inlet Nozzle Pressure represents the pressure of the incoming air or propellant before it enters the combustion chamber or the turbine section.

STEP 1: Convert Input(s) to Base Unit

Rocket Thrust: 154569.6 Newton --> 154569.6 Newton No Conversion Required
Nozzle Throat Area: 0.21 Square Meter --> 0.21 Square Meter No Conversion Required
Inlet Nozzle Pressure: 0.0037 Megapascal --> 3700 Pascal (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_F = F/(A_t*P₁) --> 154569.6/(0.21*3700)

Evaluating ... ...

C_F = 198.931274131274

STEP 3: Convert Result to Output's Unit

198.931274131274 --> No Conversion Required

FINAL ANSWER

198.931274131274 ≈ 198.9313 <-- Thrust Coefficient

(Calculation completed in 00.004 seconds)

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Created by LOKESH

Sri Ramakrishna Engineering College (SREC), COIMBATORE

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Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal

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< Nozzles Calculators

Characteristics Velocity

LaTeX Go Characteristics Velocity = sqrt((([R]*Temperature at Chamber)/Specific Heat Ratio)*((Specific Heat Ratio+1)/2)^((Specific Heat Ratio+1)/(Specific Heat Ratio-1)))

Propulsion Efficiency

LaTeX Go Propulsion Efficiency = (2*(Vehicle Speed/Exhaust Speed))/(1+(Vehicle Speed/Exhaust Speed)^2)

Specific Volume at Throat

LaTeX Go Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1))

Specific Temperature at Throat

LaTeX Go Specific Temperature = (2*Temperature at Chamber)/(Specific Heat Ratio+1)

Nozzle Thrust Coefficient Formula

LaTeX Go

Thrust Coefficient = Rocket Thrust/(Nozzle Throat Area*Inlet Nozzle Pressure)
C_F = F/(A_t*P₁)

What is Thrust Coefficient?

The thrust coefficient is a dimensionless parameter used in fluid dynamics and aerodynamics to characterize the efficiency of a propulsion system, particularly in the context of jet engines, rockets, and other propulsion devices. It represents the ratio of the actual thrust produced by the engine to the theoretical thrust it could produce under ideal conditions.

How to Calculate Nozzle Thrust Coefficient?

Nozzle Thrust Coefficient calculator uses Thrust Coefficient = Rocket Thrust/(Nozzle Throat Area*Inlet Nozzle Pressure) to calculate 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 calculate Nozzle Thrust Coefficient using this online calculator? To use this online calculator for Nozzle Thrust Coefficient, enter Rocket Thrust (F), Nozzle Throat Area (A_t) & Inlet Nozzle Pressure (P₁) and hit the calculate button. Here is how the Nozzle Thrust Coefficient calculation can be explained with given input values -> 198.9313 = 154569.6/(0.21*3700).

FAQ

What is Nozzle 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 and is represented as C_F = F/(A_t*P₁) or Thrust Coefficient = Rocket Thrust/(Nozzle Throat Area*Inlet Nozzle Pressure). Rocket Thrust determines the acceleration and performance capabilities of rocket, The nozzle throat area refers to the cross-sectional area of the narrowest part of a propulsion nozzle, known as the throat & Inlet Nozzle Pressure represents the pressure of the incoming air or propellant before it enters the combustion chamber or the turbine section.

How to calculate Nozzle 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 is calculated using Thrust Coefficient = Rocket Thrust/(Nozzle Throat Area*Inlet Nozzle Pressure). To calculate Nozzle Thrust Coefficient, you need Rocket Thrust (F), Nozzle Throat Area (A_t) & Inlet Nozzle Pressure (P₁). With our tool, you need to enter the respective value for Rocket Thrust, Nozzle Throat Area & Inlet Nozzle Pressure and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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