Ram drag Calculator

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Jet Propulsion

Components of Gas Turbine

Rocket Propulsion

Thermodynamics and Governing Equations

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Performance Parameters

Turbofans

Turbojets

Turbomachinery Equations

Turboprops

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Thrust Generation

Efficiency Metrics

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

✖Ram Drag refers to the drag force experienced by a jet engine due to the impact of air at high speeds.ⓘ Ram drag [D_ram]

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Formula

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Ram drag

Formula

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

Example

`"388.5N"="3.5kg/s"*"111m/s"`

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Ram drag Solution

STEP 0: Pre-Calculation Summary

Formula Used

Ram Drag = Mass Flow Rate*Flight Speed
D_ram = m_a*V
This formula uses 3 Variables

Variables Used

Ram Drag - (Measured in Newton) - Ram Drag refers to the drag force experienced by a jet engine due to the impact of air at high speeds.
Mass Flow Rate - (Measured in Kilogram per Second) - Mass Flow Rate represents the amount of mass passing through a system per unit of time.
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
Flight Speed: 111 Meter per Second --> 111 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

D_ram = m_a*V --> 3.5*111

Evaluating ... ...

D_ram = 388.5

STEP 3: Convert Result to Output's Unit

388.5 Newton --> No Conversion Required

FINAL ANSWER

388.5 Newton <-- Ram Drag

(Calculation completed in 00.020 seconds)

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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

Kartikay Pandit has verified this Calculator and 400+ more calculators!

< 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

Ram drag Formula

Ram Drag = Mass Flow Rate*Flight Speed
D_ram = m_a*V

What is Ram drag?

The loss of thrust in a turbofan or turbojet engine that is caused by increasing the velocity of the air entering the engine. Ram drag is the difference between gross thrust and the net thrust.

How to Calculate Ram drag?

Ram drag calculator uses Ram Drag = Mass Flow Rate*Flight Speed to calculate the Ram Drag, The Ram drag formula is defined as the second term (m dot * V) is called the ram drag and is usually associated with conditions in the inlet. For clarity, the engine thrust is then called the net thrust. Ram Drag is denoted by D_ram symbol.

How to calculate Ram drag using this online calculator? To use this online calculator for Ram drag, enter Mass Flow Rate (m_a) & Flight Speed (V) and hit the calculate button. Here is how the Ram drag calculation can be explained with given input values -> 388.5 = 3.5*111.

FAQ

What is Ram drag?

The Ram drag formula is defined as the second term (m dot * V) is called the ram drag and is usually associated with conditions in the inlet. For clarity, the engine thrust is then called the net thrust and is represented as D_ram = m_a*V or Ram Drag = Mass Flow Rate*Flight Speed. Mass Flow Rate represents the amount of mass passing through a system per unit of time & Flight Speed refers to the velocity at which an aircraft moves through the air.

How to calculate Ram drag?

The Ram drag formula is defined as the second term (m dot * V) is called the ram drag and is usually associated with conditions in the inlet. For clarity, the engine thrust is then called the net thrust is calculated using Ram Drag = Mass Flow Rate*Flight Speed. To calculate Ram drag, you need Mass Flow Rate (m_a) & Flight Speed (V). With our tool, you need to enter the respective value for Mass Flow Rate & Flight 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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