Mach Number with Fluids Solution

STEP 0: Pre-Calculation Summary
Formula Used
Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature))
M = uf/(sqrt(Y*R*Tf))
This formula uses 1 Functions, 5 Variables
Functions Used
sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)
Variables Used
Mach Number - Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
Fluid Velocity - (Measured in Meter per Second) - Fluid velocity is the volume of fluid flowing in the given vessel per unit cross sectional area.
Specific Heat Ratio - The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume.
Universal Gas Constant - Universal Gas Constant is a physical constant that appears in an equation defining the behavior of a gas under theoretically ideal conditions. Its unit is joule*kelvin−1*mole−1.
Final Temperature - (Measured in Kelvin) - Final Temperature is the measure of hotness or coldness of a system at its final state.
STEP 1: Convert Input(s) to Base Unit
Fluid Velocity: 12 Meter per Second --> 12 Meter per Second No Conversion Required
Specific Heat Ratio: 1.6 --> No Conversion Required
Universal Gas Constant: 8.314 --> No Conversion Required
Final Temperature: 345 Kelvin --> 345 Kelvin No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
M = uf/(sqrt(Y*R*Tf)) --> 12/(sqrt(1.6*8.314*345))
Evaluating ... ...
M = 0.177135944396887
STEP 3: Convert Result to Output's Unit
0.177135944396887 --> No Conversion Required
FINAL ANSWER
0.177135944396887 0.177136 <-- Mach Number
(Calculation completed in 00.004 seconds)

Credits

Created by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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K J Somaiya College of Engineering (K J Somaiya), Mumbai
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20 Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters
Go Pressure Coefficient = 2*Flow Deflection angle^2*((Specific Heat Ratio+1)/4+sqrt(((Specific Heat Ratio+1)/4)^2+1/Hypersonic Similarity Parameter^2))
Pressure Ratio having High Mach Number with Similarity Constant
Go Pressure Ratio = (1-((Specific Heat Ratio-1)/2)*Hypersonic Similarity Parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
Mach Number with Fluids
Go Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature))
Pressure Ratio for High Mach Number
Go Pressure Ratio = (Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
Moment Coefficient
Go Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length)
Deflection Angle
Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of shock-1/Mach Number behind shock)
Normal Force Coefficient
Go Coefficient of Force = Normal Force/(Dynamic Pressure*Area for Flow)
Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle
Go Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1))
Dynamic Pressure given Coefficient of Lift
Go Dynamic Pressure = Lift Force/(Lift Coefficient*Area for Flow)
Coefficient of Drag
Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area for Flow)
Dynamic Pressure
Go Dynamic Pressure = Drag Force/(Drag Coefficient*Area for Flow)
Lift Coefficient
Go Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow)
Axial Force Coefficient
Go Coefficient of Force = Force/(Dynamic Pressure*Area for Flow)
Drag Force
Go Drag Force = Drag Coefficient*Dynamic Pressure*Area for Flow
Lift Force
Go Lift Force = Lift Coefficient*Dynamic Pressure*Area for Flow
Mach Ratio at High Mach Number
Go Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2)
Hypersonic Similarity Parameter
Go Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle
Shear-Stress Distribution
Go Shear Stress = Viscosity Coefficient*Velocity Gradient
Fourier's Law of Heat Conduction
Go Heat Flux = Thermal Conductivity*Temperature Gradient
Newtonian Sine Squared Law for Pressure Coefficient
Go Pressure Coefficient = 2*sin(Deflection Angle)^2

Mach Number with Fluids Formula

Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature))
M = uf/(sqrt(Y*R*Tf))

What is a Mach number?.

Mach number is the ratio of velocity of fluid after shock to the speed of sound i the same fluid. The Mach number is primarily used to determine the approximation with which a flow can be treated as an incompressible flow. The medium can be a gas or a liquid.

How to Calculate Mach Number with Fluids?

Mach Number with Fluids calculator uses Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature)) to calculate the Mach Number, Mach Number with Fluids formula is defined as the ratio of velocity of flow after shock to the product of square root of the specific heat ratio, universal gas constant and temperature of fluid after shock. Mach Number is denoted by M symbol.

How to calculate Mach Number with Fluids using this online calculator? To use this online calculator for Mach Number with Fluids, enter Fluid Velocity (uf), Specific Heat Ratio (Y), Universal Gas Constant (R) & Final Temperature (Tf) and hit the calculate button. Here is how the Mach Number with Fluids calculation can be explained with given input values -> 0.177136 = 12/(sqrt(1.6*8.314*345)).

FAQ

What is Mach Number with Fluids?
Mach Number with Fluids formula is defined as the ratio of velocity of flow after shock to the product of square root of the specific heat ratio, universal gas constant and temperature of fluid after shock and is represented as M = uf/(sqrt(Y*R*Tf)) or Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature)). Fluid velocity is the volume of fluid flowing in the given vessel per unit cross sectional area, The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume, Universal Gas Constant is a physical constant that appears in an equation defining the behavior of a gas under theoretically ideal conditions. Its unit is joule*kelvin−1*mole−1 & Final Temperature is the measure of hotness or coldness of a system at its final state.
How to calculate Mach Number with Fluids?
Mach Number with Fluids formula is defined as the ratio of velocity of flow after shock to the product of square root of the specific heat ratio, universal gas constant and temperature of fluid after shock is calculated using Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature)). To calculate Mach Number with Fluids, you need Fluid Velocity (uf), Specific Heat Ratio (Y), Universal Gas Constant (R) & Final Temperature (Tf). With our tool, you need to enter the respective value for Fluid Velocity, Specific Heat Ratio, Universal Gas Constant & Final Temperature 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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