Stagnation Temperature Calculator
Calculate stagnation (total) temperature from velocity or Mach number in compressible flow
Calculator
Select a calculation mode and enter the required inputs to compute stagnation temperature.
About the Stagnation Temperature Calculator
The Stagnation Temperature Calculator allows you to compute the total (stagnation) temperature of a flowing gas using either velocity and specific heat or Mach number and gamma. Stagnation temperature represents the temperature a fluid would reach if it were brought to rest isentropically, and it is a key parameter in aerospace engineering, compressible flow, and gas dynamics.
What You Can Calculate
- Stagnation Temperature (T₀): Total temperature of a gas in high-speed flow.
- Dynamic Temperature Rise: Increase due to kinetic energy at velocity v.
- Isentropic Temperature Ratio: Based on Mach number and γ.
Formulas Used in the Calculator
The calculator uses standard compressible-flow equations:
- Velocity Method: T₀ = T + v² / (2cₚ)
- Mach Number Method: T₀ = T × (1 + (γ − 1)/2 × M²)
- Specific Heat (if computed): cₚ = γR / (γ − 1), with R = 287 J/kg·K
How to Use the Calculator
- Select your preferred calculation mode.
- Enter the static temperature and the required inputs for your mode.
- If using the velocity method, choose whether to enter cₚ manually or compute it from γ.
- The stagnation temperature updates instantly as you input values.
Applications of Stagnation Temperature
Stagnation temperature is a fundamental parameter in jet engines, compressor design, nozzle flow, high-speed aerodynamics, supersonic aircraft, and rocket propulsion. It helps engineers analyze thermal loads, flow energy, and temperature recovery in compressible gas flows.