Aerodynamics & Gas Dynamics
Mach Angle Simulator
Examine the geometry of supersonic flow. Change gas presets, adjust local temperature, and control Mach numbers to see shock wave cones and calculate sound speeds.
Preset
AIR
1.4 ratio
Flow Regime
Supersonic
M = 2.00
Output
CSV
Data export ready
Parameters
Gas Preset
Supersonic Mach Sweep
Aeronautical Formulas
Mach Angle
μ = arcsin(1 / M)
Speed of Sound
a = √(γ * R * T)
Flow Velocity
V = M * a
At Mach 2.00, the flow is supersonic.
The sound waves form a Mach cone with vertex angle 60.0°.
Speed of sound in Air at 25°C is 346.1 m/s.
Supersonic Wave Fronts & Cone
Mach Angle (μ)
30.00°
Cone Vertex Angle (2μ)
60.00°
Speed of Sound (a)
346.1m/s
Flow Velocity (V)
692.2m/s
Mach Cone Angle & Velocity vs Mach Number
Mach Sweep Node Data
| Mach Number (M) | Mach Angle μ (°) | Cone Angle 2μ (°) | Flow Velocity (m/s) |
|---|---|---|---|
| 1.05 | 72.25 | 144.49 | 363.4 |
| 1.51 | 41.36 | 82.72 | 523.8 |
| 1.98 | 30.39 | 60.78 | 684.2 |
| 2.44 | 24.19 | 48.39 | 844.5 |
| 2.90 | 20.15 | 40.29 | 1004.9 |
| 3.37 | 17.28 | 34.56 | 1165.3 |
| 3.83 | 15.14 | 30.27 | 1325.6 |
| 4.29 | 13.47 | 26.94 | 1486.0 |
| 4.76 | 12.14 | 24.27 | 1646.4 |
| 5.22 | 11.04 | 22.09 | 1806.7 |
| 5.68 | 10.13 | 20.27 | 1967.1 |
| 6.15 | 9.36 | 18.73 | 2127.5 |
| 6.61 | 8.70 | 17.40 | 2287.8 |
| 7.07 | 8.13 | 16.25 | 2448.2 |
| 7.54 | 7.62 | 15.25 | 2608.6 |
| 8.00 | 7.18 | 14.36 | 2768.9 |