๐ฅ Compressible Rayleigh Flow (Heat Addition)
Evaluate 1D compressible flow with heat addition or combustion, computing exit Mach (M2), thermal choking limit (q_max), stagnation pressure loss, and entropy generation.
โก Fortran 90 Engine
Double Precision (IEEE 754)
โ ISO / ASME Validated
Cfd
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โก Solves
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๐พ Downloads
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๐ฆ Fortran Code
4.4 KB
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Released
Jun 2026
โฑ๏ธ Latency
< 1 ms
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๐ฅ Combustor Duct Thermal Expansion & Thermal Choking (M = 1.0)
Real-time visual simulation of flame heat zone, thermal acceleration & Rayleigh entropy increase๐ Configuration & Presets
โก Gas Turbine Combustor
๐ Ramjet Afterburner
โ๏ธ Scramjet (M = 2.4)
๐ญ Furnace Burner Duct
Rayleigh Flow Formulations:
โข Stagnation Temp Ratio: Tโ/Tโ* = 2(ฮณ+1)Mยฒ (1 + ยฝ(ฮณโ1)Mยฒ) / (1 + ฮณMยฒ)ยฒ
โข Max Heat Addition: qmax = cp (Tโ* โ Tโโ) [kJ/kg]
โข Heat addition accelerates subsonic flow toward M=1 and decelerates supersonic flow.
โข Total Pressure Loss: ฮPโ is unavoidable during heat addition at high speed.
โข Stagnation Temp Ratio: Tโ/Tโ* = 2(ฮณ+1)Mยฒ (1 + ยฝ(ฮณโ1)Mยฒ) / (1 + ฮณMยฒ)ยฒ
โข Max Heat Addition: qmax = cp (Tโ* โ Tโโ) [kJ/kg]
โข Heat addition accelerates subsonic flow toward M=1 and decelerates supersonic flow.
โข Total Pressure Loss: ฮPโ is unavoidable during heat addition at high speed.
๐ Rayleigh Flow Results
Configure inputs and click Compute to view results.
๐ Calculation Methodology & Rayleigh Flow Standards
Thermal Choking Limit
Adding heat to a subsonic compressible flow increases Mach number and entropy up to the sonic point $M=1$. Exceeding $q_{max}$ causes thermal choking:
qmax = cp (Tโ* โ Tโโ)
Combustion Total Pressure Loss
Fundamental momentum conservation dictates that adding thermal energy to a high-speed gas creates an unavoidable fundamental total pressure drop $\Delta P_0$.
Key Engineering Assumptions
- 1D steady frictionless flow in constant cross-sectional area duct.
- Uniform thermal energy addition across the stream.
- Ideal gas with constant average $c_p$ and $\gamma$.