Inlet drag Calculator

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Components of Gas Turbine

Jet Propulsion

Rocket Propulsion

Thermodynamics and Governing Equations

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✖Mass flow rate of air is the mass flow rate of air.ⓘ Mass Flow Rate of Air [m_a]			+10% -10%
✖Aircraft forward speed the speed at which aircraft is moving.ⓘ Aircraft Forward Speed [V]			+10% -10%

✖Inlet drag is the aerodynamic force that opposes an aircraft's motion.ⓘ Inlet drag [F_D]

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Formula

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Inlet drag

Formula

`"F"_{"D"} = "m"_{"a"}*"V"`

Example

`"434N"="3.5kg/s"*"124m/s"`

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Inlet drag Solution

STEP 0: Pre-Calculation Summary

Formula Used

Inlet drag = Mass Flow Rate of Air*Aircraft Forward Speed
F_D = m_a*V
This formula uses 3 Variables

Variables Used

Inlet drag - (Measured in Newton) - Inlet drag is the aerodynamic force that opposes an aircraft's motion.
Mass Flow Rate of Air - (Measured in Kilogram per Second) - Mass flow rate of air is the mass flow rate of air.
Aircraft Forward Speed - (Measured in Meter per Second) - Aircraft forward speed the speed at which aircraft is moving.

STEP 1: Convert Input(s) to Base Unit

Mass Flow Rate of Air: 3.5 Kilogram per Second --> 3.5 Kilogram per Second No Conversion Required
Aircraft Forward Speed: 124 Meter per Second --> 124 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_D = m_a*V --> 3.5*124

Evaluating ... ...

F_D = 434

STEP 3: Convert Result to Output's Unit

434 Newton --> No Conversion Required

FINAL ANSWER

434 Newton <-- Inlet drag

(Calculation completed in 00.020 seconds)

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Credits

Created by Chilvera Bhanu Teja

Institute of Aeronautical Engineering (IARE), Hyderabad

Chilvera Bhanu Teja has created this Calculator and 300+ more calculators!

Verified by Vaibhav Malani

National Institute of Technology (NIT), Tiruchirapalli

Vaibhav Malani has verified this Calculator and 200+ more calculators!

< 4 Inlets Calculators

Diffuser Efficiency given Inlet and Exit Velocities

Go Diffuser Efficiency = Actual Static Pressure Rise/(Density of Air/2*(Inlet Velocity to Diffuser^2-Exit Velocity to Diffuser^2))

Diffuser Efficiency

Go Diffuser Efficiency = Actual Static Pressure Rise/Isentropic Static Pressure Rise

Kinetic Energy of Air at Inlet

Go Kinetic Energy = 1/2*Mass Flow Rate of Air*Aircraft Forward Speed^2

Inlet drag

Go Inlet drag = Mass Flow Rate of Air*Aircraft Forward Speed

Inlet drag Formula

Inlet drag = Mass Flow Rate of Air*Aircraft Forward Speed
F_D = m_a*V

What is drag?

Drag is the aerodynamic force that opposes an aircraft's motion through the air. Drag is a mechanical force. It is generated by the interaction and contact of a solid body with a fluid (liquid or gas).

How to Calculate Inlet drag?

Inlet drag calculator uses Inlet drag = Mass Flow Rate of Air*Aircraft Forward Speed to calculate the Inlet drag, The Inlet drag formula is defined as the product of the mass flow rate of air and forward speed of aircraft. Inlet drag is denoted by F_D symbol.

How to calculate Inlet drag using this online calculator? To use this online calculator for Inlet drag, enter Mass Flow Rate of Air (m_a) & Aircraft Forward Speed (V) and hit the calculate button. Here is how the Inlet drag calculation can be explained with given input values -> 434 = 3.5*124.

FAQ

What is Inlet drag?

The Inlet drag formula is defined as the product of the mass flow rate of air and forward speed of aircraft and is represented as F_D = m_a*V or Inlet drag = Mass Flow Rate of Air*Aircraft Forward Speed. Mass flow rate of air is the mass flow rate of air & Aircraft forward speed the speed at which aircraft is moving.

How to calculate Inlet drag?

The Inlet drag formula is defined as the product of the mass flow rate of air and forward speed of aircraft is calculated using Inlet drag = Mass Flow Rate of Air*Aircraft Forward Speed. To calculate Inlet drag, you need Mass Flow Rate of Air (m_a) & Aircraft Forward Speed (V). With our tool, you need to enter the respective value for Mass Flow Rate of Air & Aircraft Forward Speed 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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