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Mach Number-2 Formula:
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The Mach Number-2 formula calculates the downstream Mach number in compressible flow systems. It relates the upstream Mach number (Mr) and the heat capacity ratio (Y) to determine the Mach number at a downstream point in the flow field.
The calculator uses the Mach Number-2 formula:
Where:
Explanation: This formula calculates the Mach number at a downstream point based on the upstream Mach number and the heat capacity ratio of the fluid.
Details: Accurate Mach number calculation is crucial for analyzing compressible flow systems, designing aerodynamic components, and understanding shock wave behavior in fluid dynamics.
Tips: Enter the upstream Mach number and heat capacity ratio. Both values must be positive numbers. The heat capacity ratio typically ranges from 1.0 to 1.67 for common gases.
Q1: What is Mach number?
A: Mach number is a dimensionless quantity that represents the ratio of an object's speed to the speed of sound in the surrounding medium.
Q2: What is the heat capacity ratio?
A: The heat capacity ratio (also known as the adiabatic index) is the ratio of specific heats at constant pressure to constant volume for a given gas.
Q3: What are typical values for heat capacity ratio?
A: For air at standard conditions, Y ≈ 1.4; for monatomic gases like helium, Y ≈ 1.67; for diatomic gases, Y ≈ 1.4.
Q4: When is this formula applicable?
A: This formula is used in compressible flow analysis, particularly for normal shock wave calculations and flow through nozzles and diffusers.
Q5: Are there limitations to this equation?
A: The formula assumes ideal gas behavior and is valid for one-dimensional, steady, adiabatic flow with no external work or heat transfer.