Flight Speed given Ideal Thrust Solution

STEP 0: Pre-Calculation Summary
Formula Used
Flight Speed = Exit Velocity-Ideal Thrust/Mass Flow Rate
V = Ve-Tideal/ma
This formula uses 4 Variables
Variables Used
Flight Speed - (Measured in Meter per Second) - Flight Speed refers to the velocity at which an aircraft moves through the air.
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.
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.
STEP 1: Convert Input(s) to Base Unit
Exit Velocity: 248 Meter per Second --> 248 Meter per Second No Conversion Required
Ideal Thrust: 479.5 Newton --> 479.5 Newton No Conversion Required
Mass Flow Rate: 3.5 Kilogram per Second --> 3.5 Kilogram per Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
V = Ve-Tideal/ma --> 248-479.5/3.5
Evaluating ... ...
V = 111
STEP 3: Convert Result to Output's Unit
111 Meter per Second --> No Conversion Required
FINAL ANSWER
111 Meter per Second <-- Flight Speed
(Calculation completed in 00.004 seconds)

Credits

Created by Himanshu Sharma
National Institute of Technology, Hamirpur (NITH), Himachal Pradesh
Himanshu Sharma has created this Calculator and 50+ more calculators!
Verified by Kartikay Pandit
National Institute Of Technology (NIT), Hamirpur
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21 Thrust Generation Calculators

Total Thrust given Efficiency and Enthalpy
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)))
Momentum Thrust
Go Ideal Thrust = Mass Flow Rate*((1+Fuel Air Ratio)*Exit Velocity-Flight Speed)
Thrust power
Go Thrust Power = Mass Flow Rate*Flight Speed*(Exit Velocity-Flight Speed)
Ideal Thrust given Effective Speed Ratio
Go Ideal Thrust = Mass Flow Rate*Flight Speed*((1/Effective Speed Ratio)-1)
Thrust given aircraft forward speed, velocity of exhaust
Go Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed)
Mass Flow Rate given Ideal Thrust
Go Mass Flow Rate = Ideal Thrust/(Exit Velocity-Flight Speed)
Ideal Thrust of Jet Engine
Go Ideal Thrust = Mass Flow Rate*(Exit Velocity-Flight Speed)
Velocity after Expansion given Ideal Thrust
Go Exit Velocity = Ideal Thrust/Mass Flow Rate+Flight Speed
Flight Speed given Ideal Thrust
Go Flight Speed = Exit Velocity-Ideal Thrust/Mass Flow Rate
Thrust specific fuel consumption
Go Thrust-Specific Fuel Consumption = (3600*Fuel Air Ratio)/Specific Thrust
Thrust power specific fuel consumption
Go Thrust Power Specific Fuel Consumption = Fuel Flow Rate/Thrust Power
Gross Thrust Coefficient
Go Gross Thrust Coefficient = Gross Thrust/Ideal Gross Thrust
Specific Thrust given Effective Speed Ratio
Go Specific Thrust = Exit Velocity*(1-Effective Speed Ratio)
Flight Speed given Momentum of Ambient Air
Go Flight Speed = Momentum of Ambient Air/Mass Flow Rate
Mass Flow given Momentum in Ambient Air
Go Mass Flow Rate = Momentum of Ambient Air/Flight Speed
Momentum of Ambient Air
Go Momentum of Ambient Air = Mass Flow Rate*Flight Speed
Specific thrust
Go Specific Thrust = Exit Velocity-Flight Speed
Gross thrust
Go Gross Thrust = Mass Flow Rate*Exit Velocity
Mass Flow Rate given Ram Drag and Flight Speed
Go Mass Flow Rate = Ram Drag/Flight Speed
Flight Speed given Ram Drag and Mass Flow Rate
Go Flight Speed = Ram Drag/Mass Flow Rate
Ram drag
Go Ram Drag = Mass Flow Rate*Flight Speed

Flight Speed given Ideal Thrust Formula

Flight Speed = Exit Velocity-Ideal Thrust/Mass Flow Rate
V = Ve-Tideal/ma

What is flight speed?

In aviation, V-speeds are standard terms used to define airspeeds important or useful to the operation of all aircraft. These speeds are derived from data obtained by aircraft designers and manufacturers during flight testing for aircraft type-certification.

How to Calculate Flight Speed given Ideal Thrust?

Flight Speed given Ideal Thrust calculator uses Flight Speed = Exit Velocity-Ideal Thrust/Mass Flow Rate to calculate the Flight Speed, The flight speed given ideal thrust formula is defined as speed of the aircraft after the perfect expansion of gases in the nozzle. Flight Speed is denoted by V symbol.

How to calculate Flight Speed given Ideal Thrust using this online calculator? To use this online calculator for Flight Speed given Ideal Thrust, enter Exit Velocity (Ve), Ideal Thrust (Tideal) & Mass Flow Rate (ma) and hit the calculate button. Here is how the Flight Speed given Ideal Thrust calculation can be explained with given input values -> 118.5714 = 248-479.5/3.5.

FAQ

What is Flight Speed given Ideal Thrust?
The flight speed given ideal thrust formula is defined as speed of the aircraft after the perfect expansion of gases in the nozzle and is represented as V = Ve-Tideal/ma or Flight Speed = Exit Velocity-Ideal Thrust/Mass Flow Rate. Exit Velocity refers to the speed at which gases expand at the exit of nozzle of a engine, 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 represents the amount of mass passing through a system per unit of time.
How to calculate Flight Speed given Ideal Thrust?
The flight speed given ideal thrust formula is defined as speed of the aircraft after the perfect expansion of gases in the nozzle is calculated using Flight Speed = Exit Velocity-Ideal Thrust/Mass Flow Rate. To calculate Flight Speed given Ideal Thrust, you need Exit Velocity (Ve), Ideal Thrust (Tideal) & Mass Flow Rate (ma). With our tool, you need to enter the respective value for Exit Velocity, Ideal Thrust & Mass Flow Rate 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 Flight Speed?
In this formula, Flight Speed uses Exit Velocity, Ideal Thrust & Mass Flow Rate. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Flight Speed = Momentum of Ambient Air/Mass Flow Rate
  • Flight Speed = Ram Drag/Mass Flow Rate
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