Credits

Defence institute of advanced technology (DRDO) (DIAT), pune
Abhinav Gupta has created this Calculator and 25+ more calculators!
National Institute of Technology Calicut (NIT Calicut), Calicut, Kerala
Peri Krishna Karthik has verified this Calculator and 8 more calculators!

Mach Number-2 Solution

STEP 0: Pre-Calculation Summary
Formula Used
Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach number^(2)+2))/(2*Heat Capacity Ratio*Mach number^(2)-(Heat Capacity Ratio-1))))
M = sqrt(((((γ-1)*M^(2)+2))/(2*γ*M^(2)-(γ-1))))
This formula uses 1 Functions, 2 Variables
Functions Used
sqrt - Squre root function, sqrt(Number)
Variables Used
Heat Capacity Ratio- The heat capacity ratio also known as the adiabatic index is the ratio of specific heats i.e. the ratio of the heat capacity at constant pressure to heat capacity at constant volume.
Mach number- The Mach number is a dimensionless quantity in fluid dynamics representing the ratio of flow velocity past a boundary to the local speed of sound.
STEP 1: Convert Input(s) to Base Unit
Heat Capacity Ratio: 1.4 --> No Conversion Required
Mach number: 1.1 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
M = sqrt(((((γ-1)*M^(2)+2))/(2*γ*M^(2)-(γ-1)))) --> sqrt(((((1.4-1)*1.1^(2)+2))/(2*1.4*1.1^(2)-(1.4-1))))
Evaluating ... ...
M = 0.911770421325905
STEP 3: Convert Result to Output's Unit
0.911770421325905 --> No Conversion Required
FINAL ANSWER
0.911770421325905 <-- Mach number 2
(Calculation completed in 00.000 seconds)

10+ Material Science and Metallurgy Calculators

Mach Number-2
Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach number^(2)+2))/(2*Heat Capacity Ratio*Mach number^(2)-(Heat Capacity Ratio-1)))) Go
Zero bias junction voltage
Zero bias junction voltage = Thermal voltage*ln(Impurity Concentration In Solid/Intrinsic Concentration^2) Go
Bending stress in beam calculator
Bending Stress = (3*Load*Length of beam)/(2*Width*(Thickness of Beam^2)) Go
Shock strength of two pressure
Shock Strength = (Initial Pressure of System-Final Pressure of System)/Final Pressure of System Go
Shock strength of moving object
Shock Strength = (2*Heat Capacity Ratio)/((Heat Capacity Ratio+1)*(Mach number^2-1)) Go
Spindle speed
Spindle speed = Cutting Speed*1000/(pi*Diameter of a Cutting Tool) Go
Length of Filament in 3-D printing
Length of filament = Weight/(Density*Cross Sectional Area) Go
Feed per tooth
Feed per tooth = Feed/(Number of teeth*Spindle speed) Go
Poisson Ratio
Poisson's Ratio = Lateral Strain/Longitudinal Strain Go
Mach number of moving object
Mach number = Velocity/Speed of Sound Go

Mach Number-2 Formula

Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach number^(2)+2))/(2*Heat Capacity Ratio*Mach number^(2)-(Heat Capacity Ratio-1))))
M = sqrt(((((γ-1)*M^(2)+2))/(2*γ*M^(2)-(γ-1))))

Relationship between mach number 2 and mach number 1

Mach number 1 or Mach number 2 can be calculated with the help of relationship between themThe Mach number due to the local speed of sound is dependent on the surrounding mediums in specific temperature and pressure. Flow can be determined as an incompressible flow with the help of the Mach number. The medium can either be a liquid or a gas. The medium can be flowing, whereas the boundary may be stable or the boundary may be travelling in a medium that is at rest. The medium and boundary both may be travelling with a certain speed, but their velocities with respect to each other are what matters. The medium may be channelled through several devices such as wind tunnels or may be immersed in the medium. The Mach number is termed as a dimensionless number because it is a ratio of two speeds

Classification of Mach number as per range

Subsonic:
Commercial aircraft with aerodynamic features such as the rounded nose and leading edges. The Mach is below 0.8.

Transonic:
Aircraft that are built with swept wings. The Mach value is between 0.8-2.1.

Supersonic:
The aircraft created to go supersonic have a definite design, it has the complete movement of the canards, thin aerofoil sections, and sharp edges. The Mach levels are between 1.2 and 5.0.

Hypersonic:
These planes have several distinctive features such as nickel-titanium skin that is cooled and small wings. The Mach values are between 5.0 and 10.0. The U.S. plane X-15 created the world record of flying at Mach 6.72.

High-Hypersonic:
The Mach levels are between 10.0 -25.0. When flying at such huge speeds thermal controls becomes an integral portion of the design. The hotness of the surface must be considered beforehand.

Re-entry speeds:
The Mach speed is above 25.0. This does not require wings and a blunt design.

How to Calculate Mach Number-2?

Mach Number-2 calculator uses Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach number^(2)+2))/(2*Heat Capacity Ratio*Mach number^(2)-(Heat Capacity Ratio-1)))) to calculate the Mach number 2, The Mach Number-2 is calculated with the help of an established relationship between mach number 1 and mach number 2. Mach number 2 is denoted by M symbol.

How to calculate Mach Number-2 using this online calculator? To use this online calculator for Mach Number-2, enter Heat Capacity Ratio (γ) & Mach number (M) and hit the calculate button. Here is how the Mach Number-2 calculation can be explained with given input values -> 0.91177 = sqrt(((((1.4-1)*1.1^(2)+2))/(2*1.4*1.1^(2)-(1.4-1)))).

FAQ

What is Mach Number-2?
The Mach Number-2 is calculated with the help of an established relationship between mach number 1 and mach number 2 and is represented as M = sqrt(((((γ-1)*M^(2)+2))/(2*γ*M^(2)-(γ-1)))) or Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach number^(2)+2))/(2*Heat Capacity Ratio*Mach number^(2)-(Heat Capacity Ratio-1)))). The heat capacity ratio also known as the adiabatic index is the ratio of specific heats i.e. the ratio of the heat capacity at constant pressure to heat capacity at constant volume & The Mach number is a dimensionless quantity in fluid dynamics representing the ratio of flow velocity past a boundary to the local speed of sound.
How to calculate Mach Number-2?
The Mach Number-2 is calculated with the help of an established relationship between mach number 1 and mach number 2 is calculated using Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach number^(2)+2))/(2*Heat Capacity Ratio*Mach number^(2)-(Heat Capacity Ratio-1)))). To calculate Mach Number-2, you need Heat Capacity Ratio (γ) & Mach number (M). With our tool, you need to enter the respective value for Heat Capacity Ratio & Mach number and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
Share Image
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!