Thrust given aircraft forward speed, velocity of exhaust Calculator

✖Mass Flow Rate represents the amount of mass passing through a system per unit of time.ⓘ Mass Flow Rate [m_a]			+10% -10%
✖Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a engine.ⓘ Exit Velocity [V_e]			+10% -10%
✖Flight Speed refers to the velocity at which an aircraft moves through the air.ⓘ Flight Speed [V]			+10% -10%

✖Ideal Thrust is the thrust produced by an engine when nozzle exit pressure is same as ambient pressure or nozzle is perfectly expanded.ⓘ Thrust given aircraft forward speed, velocity of exhaust [T_ideal]

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Thrust given aircraft forward speed, velocity of exhaust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed)
T_ideal = m_a*(V_e-V)
This formula uses 4 Variables

Variables Used

Ideal Thrust - (Measured in Newton) - Ideal Thrust is the thrust produced by an engine when nozzle exit pressure is same as ambient pressure or nozzle is perfectly expanded.
Mass Flow Rate - (Measured in Kilogram per Second) - Mass Flow Rate represents the amount of mass passing through a system per unit of time.
Exit Velocity - (Measured in Meter per Second) - Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a engine.
Flight Speed - (Measured in Meter per Second) - Flight Speed refers to the velocity at which an aircraft moves through the air.

STEP 1: Convert Input(s) to Base Unit

Mass Flow Rate: 3.5 Kilogram per Second --> 3.5 Kilogram per Second No Conversion Required
Exit Velocity: 248 Meter per Second --> 248 Meter per Second No Conversion Required
Flight Speed: 111 Meter per Second --> 111 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T_ideal = m_a*(V_e-V) --> 3.5*(248-111)

Evaluating ... ...

T_ideal = 479.5

STEP 3: Convert Result to Output's Unit

479.5 Newton --> No Conversion Required

FINAL ANSWER

479.5 Newton <-- Ideal Thrust

(Calculation completed in 00.010 seconds)

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Institute of Aeronautical Engineering (IARE), Hyderabad

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< Thrust Generation Calculators

Total Thrust given Efficiency and Enthalpy

LaTeX Go Total Thrust = Mass Flow Rate*((sqrt(2*Enthalpy Drop in Nozzle*Nozzle Efficiency))-Flight Speed+(sqrt(Turbine Efficiency*Efficiency of Transmission*Enthalpy Drop in Turbine)))

Thrust power

LaTeX Go Thrust Power = Mass Flow Rate*Flight Speed*(Exit Velocity-Flight Speed)

Ideal Thrust given Effective Speed Ratio

LaTeX Go Ideal Thrust = Mass Flow Rate*Flight Speed*((1/Effective Speed Ratio)-1)

Specific thrust

LaTeX Go Specific Thrust = Exit Velocity-Flight Speed

Thrust given aircraft forward speed, velocity of exhaust Formula

LaTeX Go

Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed)
T_ideal = m_a*(V_e-V)

What is thrust?

Thrust is the force which moves an aircraft through the air. Thrust is used to overcome the drag of an airplane, and to overcome the weight of a rocket.

How to Calculate Thrust given aircraft forward speed, velocity of exhaust?

Thrust given aircraft forward speed, velocity of exhaust calculator uses Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed) to calculate the Ideal Thrust, Thrust given aircraft forward speed, velocity of exhaust is a measure of the maximum forward force produced by an aircraft, calculated by considering the mass flow rate, the exhaust velocity and aircraft's forward speed. Ideal Thrust is denoted by T_ideal symbol.

How to calculate Thrust given aircraft forward speed, velocity of exhaust using this online calculator? To use this online calculator for Thrust given aircraft forward speed, velocity of exhaust, enter Mass Flow Rate (m_a), Exit Velocity (V_e) & Flight Speed (V) and hit the calculate button. Here is how the Thrust given aircraft forward speed, velocity of exhaust calculation can be explained with given input values -> 479.5 = 3.5*(248-111).

FAQ

What is Thrust given aircraft forward speed, velocity of exhaust?

Thrust given aircraft forward speed, velocity of exhaust is a measure of the maximum forward force produced by an aircraft, calculated by considering the mass flow rate, the exhaust velocity and aircraft's forward speed and is represented as T_ideal = m_a*(V_e-V) or Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed). Mass Flow Rate represents the amount of mass passing through a system per unit of time, Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a engine & Flight Speed refers to the velocity at which an aircraft moves through the air.

How to calculate Thrust given aircraft forward speed, velocity of exhaust?

Thrust given aircraft forward speed, velocity of exhaust is a measure of the maximum forward force produced by an aircraft, calculated by considering the mass flow rate, the exhaust velocity and aircraft's forward speed is calculated using Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed). To calculate Thrust given aircraft forward speed, velocity of exhaust, you need Mass Flow Rate (m_a), Exit Velocity (V_e) & Flight Speed (V). With our tool, you need to enter the respective value for Mass Flow Rate, Exit Velocity & Flight Speed and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Ideal Thrust?

In this formula, Ideal Thrust uses Mass Flow Rate, Exit Velocity & Flight Speed. We can use 3 other way(s) to calculate the same, which is/are as follows -

Ideal Thrust = Mass Flow Rate*Flight Speed*((1/Effective Speed Ratio)-1)
Ideal Thrust = Mass Flow Rate*((1+Fuel Air Ratio)*Exit Velocity-Flight Speed)
Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed)

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