Rocket Plume Shock Diamonds & Supersonic Turbulence Lab

Nozzle & Atmospheric Controls Prandtl-Meyer Physics

Chamber Pressure (P_c) 7.50 MPa

Ambient Pressure (P_a) 101.30 kPa

Area Expansion Ratio (A_e/A*) 15.0

Chamber Temp (T_c) 3200 K

Boundary Layer Shear & Turbulence 65 %

Sea-Level Over-Expanded Flow

When exit pressure (P_e) is less than atmospheric pressure (P_a), oblique shock waves form at the nozzle lip, compressing the gas inward and creating a chain of luminescent shock diamonds and Mach disks.

NOZZLE EXIT MACH NUMBER (M_e)

M 3.20

EXIT PRESSURE RATIO (P_e / P_a)

0.48 (Over-Expanded)

FLOW VELOCITY: 2,840 m/s

SHOCK SPACING: 42.5 px

Click or Drag on Plume canvas to drop Diagnostic Sensor Probe

Diagnostic Probe Telemetry Probe: [X: 180px, Y: 0px]

LOCAL MACH NUMBER

3.18

STATIC PRESSURE (kPa)

48.6 kPa

PLUME TEMPERATURE

1,840 K

TURBULENT VORTICITY

142.5 s⁻¹

Acoustic Shear PSD Spectrum FFT Turbulence

PEAK ACOUSTIC POWER

162.4 dB (OASPL)

STROUHAL NUMBER (Sr)

0.21 (Shear Layer Peak)

Telemetry Data Handoff

Ready for telemetry recording...

Captures dynamic flow velocity vectors, Prandtl-Meyer expansion fan angles, shock diamond spatial cadence, and acoustic shear layer power spectrum.