Stainless Steel Shock Tube Duct
High-pressure driver section (1.5 m) and driven section (6.0 m) with 75 mm internal bore.
Aerospace & Aeronautical Engineering / Shock Tube Dynamics
FREE TO EXPLORELABORATORY 18 · AEROSPACE & AERONAUTICAL ENGINEERING
Shock Tube Unsteady Wave Propagation and Contact Surface Tracking
Determine incident planar shock wave speed and pressure jump in a diaphragm-driven shock tube as a function of driver-to-driven gas pressure ratio P_4 / P_1. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
INCIDENT SHOCK MACH M_S—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with x = 0.35 dimensionless.
Adjust x, then execute aerospace trial.
Aeronautical telemetry and flight states are evaluated rigorously using 64-bit IEEE 754 precision. Residuals reflect ordinary least-squares regression across successive observations. Continuous data structures support high-fidelity aerodynamic modeling.
Aeronautical assumptions and boundary condition limits
Non-ideal finite diaphragm opening time causes shock formation over a finite distance (~5-10 tube diameters). Linear regression of the incident shock Mach increment against the acoustic pressure parameter yields a coupling slope m = 1.8500 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Solenoid-Driven Diaphragm Piercing Mechanism
Cross-shaped pneumatic cutter pierces aluminum diaphragms at precise target pressures.
High-Frequency PCB Piezoelectric Pressure Sensors
Flush-mounted pressure sensors with 1 microsecond rise time and 500 kHz resonant frequency.
Precision Digital Time-Interval Counter
Measures shock time-of-flight between sensor stations with 10 nanosecond resolution.
Helium / Nitrogen Driver Gas Manifold
Supplies high-speed of sound driver gas (helium) and driven gas (air/nitrogen) up to 50 bar.
High-Speed Transient Digital Oscilloscope
Captures raw voltage step traces showing incident shock, contact surface, and reflected shock waves.
FOLLOW THE METHOD
A reason behind every step.
Determine incident planar shock wave speed and pressure jump in a diaphragm-driven shock tube as a function of driver-to-driven gas pressure ratio P_4 / P_1. Standardized parameter settings: 0.15, 0.25, 0.38, 0.5, 0.65, 0.8 dimensionless.
01
Diaphragm Clamping and Evacuation
Clamp a pre-scored aluminum diaphragm between flanges and evacuate the driven section to initial pressure P_1 = 10 kPa.
02
Driver Section Charging
Charge the driver section with nitrogen to pressure P_4, setting target pressure ratios corresponding to parameter x = 0.15 to 0.80.
03
Diaphragm Rupture Execution
Trigger the pneumatic piercer to burst the diaphragm, generating an unsteady planar shock wave and backward expansion fan.
04
Time-of-Flight Recording
Record the trigger timestamps as the shock front passes sensor stations spaced Delta x = 1.0 m apart.
05
Shock Speed and Mach Calculation
Compute shock propagation speed V_s = Delta x / Delta t and incident shock Mach number M_s = V_s / a_1.
06
Shock Tube Equation Regression
Plot (M_s - 1.0) versus acoustic parameter x, perform linear regression to determine coupling slope m, and verify 1D gasdynamics.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Shock Tube Dynamics mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
(M_s - 1.0) \approx m \cdot \left[\left(\frac{P_4}{P_1}\right)^{\frac{\gamma-1}{2\gamma}} - 1\right] \implies (M_s - 1) = m \cdot x + b
| # | Driver Pressure Parameter (dimensionless) | Incident Shock Mach M_s (dimensionless) | Acoustic Pressure Parameter (P_4/P_1)^0.143 - 1 | Incident Shock Mach Increment (M_s - 1.0) | Remove |
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