Compressible Flow Mach Number Calculator

Calculate Mach number Ma = V/a where speed of sound a = √(γRT). Apply isentropic relations: T_0/T = 1 + (γ−1)/2 × Ma². Classify flow: subsonic (Ma<1), transonic, supersonic, hypersonic (Ma>5).

2D stress state at a point. All stresses in MPa.

σx — Normal Stress X (MPa)
σy — Normal Stress Y (MPa)
τxy — Shear Stress (MPa)
⚙ Mechanical Note: Results are based on standard textbook formulas and ISO/AASHTO references. Always verify critical designs with applicable codes (ISO 898, AASHTO 1993, AISC, Eurocode 3) and a qualified engineer.
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How to Use

Enter the values for the patient or scenario you are assessing. Calculate Mach number Ma = V/a where speed of sound a = √(γRT). Apply isentropic relations: T_0/T = 1 + (γ−1)/2 × Ma². Classify flow: subsonic (Ma<1), transonic, supersonic, hypersonic (Ma>5). Use the mach number result to inform your clinical assessment.

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