In this compressible flow calculator, we will show you how to find stagnation temperature, pressure, and density in just a few seconds.
We’ll also help you understand what compressible flow means, the formulas behind it, and why it’s important in real-world applications.
What is compressible flow?
How are stagnation and static properties related?
How do we calculate them using the Mach number? Find all the answers here!
Compressible Flow Calculator
Calculate stagnation properties for isentropic flow
Detailed Formula Explanation
In isentropic flow, fluid properties like temperature, pressure, and density change with the Mach number (M) — assuming no heat transfer, friction, or shock. Here are the three key relations:
1. Stagnation Temperature (T₀)
Formula: T₀ / T = 1 + ((γ − 1) / 2) × M²
Explanation: This shows how temperature increases with Mach number. As a fluid moves faster (higher M), kinetic energy converts into internal energy, raising the stagnation temperature.
2. Stagnation Pressure (P₀)
Formula: P₀ / P = [1 + ((γ − 1) / 2) × M²]γ/(γ−1)
Explanation: This relation connects static and stagnation pressures. It’s vital for determining how pressure changes during isentropic compression or expansion in ducts or nozzles.
3. Stagnation Density (ρ₀)
Formula: ρ₀ / ρ = [1 + ((γ − 1) / 2) × M²]1/(γ−1)
Explanation: This formula helps find how density varies with Mach number under isentropic flow, crucial for determining mass flow rates in compressible systems.
Real-World Applications
🚀 Jet Engines
Stagnation properties are used to calculate pressure and temperature at the compressor and turbine stages to ensure efficient thrust generation.
✈️ Supersonic Aircraft
Used to analyze how air properties change across diffusers and nozzles to maintain engine performance at high Mach numbers.
⚙️ Wind Tunnels
Engineers use these relations to simulate and measure air conditions around models for aerodynamic testing and validation.
🛰️ Rocket Propulsion
Isentropic flow relations are used in rocket nozzle design to predict how exhaust gases expand and accelerate, directly determining the thrust and efficiency of the rocket engine.
Example Problem: Finding Stagnation Temperature
Problem: Air flows at a Mach number of 2 with a static temperature of 300 K. Find the stagnation temperature (T₀). Take γ = 1.4.
Step 1: Write the formula
T₀ / T = 1 + ((γ − 1) / 2) × M²
Step 2: Substitute values
T₀ / 300 = 1 + ((1.4 − 1) / 2) × 2²
Step 3: Simplify the equation
T₀ / 300 = 1 + (0.4 / 2) × 4 = 1 + 0.8 = 1.8
Step 4: Solve for T₀
T₀ = 1.8 × 300 = 540 K
Final Answer: The stagnation temperature (T₀) is 540 K.
Reference Table – Isentropic Flow Symbols & Meanings
This table helps relate all key parameters used in isentropic flow equations.
FAQs
What is compressible flow?
It is when the density of air (or gas) changes because of high speed or pressure.
What is the difference between compressible and incompressible flow?
In compressible flow, the air’s density changes with speed and pressure. In incompressible flow, the density stays almost the same like how water usually behaves.
What are stagnation properties?
Stagnation properties (temperature, pressure, and density) show what the values would be if the flow slowed down to rest without losing energy.