Supersonic de Laval Nozzle Assembly
Precision CNC-machined nozzle (throat width 15 mm, depth 25 mm) with calibrated divergent contour.
Aerospace & Aeronautical Engineering / Supersonic de Laval Nozzle
FREE TO EXPLORELABORATORY 11 · AEROSPACE & AERONAUTICAL ENGINEERING
Converging-Diverging (de Laval) Nozzle Mach-Area Expansion
Validate the isentropic area-Mach number relation (A/A*) in a supersonic de Laval nozzle and determine supersonic Mach expansion across nozzle area ratios. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
SUPERSONIC MACH NUMBER M—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with A/A* = 1.5 dimensionless.
Adjust A/A*, 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
Boundary layer displacement thickness on divergent walls constricts aerodynamic area, slightly reducing Mach number below geometric A/A*. Linear regression of Mach increment against area ratio increment yields a supersonic expansion slope of 0.8500 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
High-Pressure Air Storage Reservoir (1.0 MPa)
Pressurized dry air bank delivering stable stagnation pressure P_0 up to 10 bar.
Multi-Channel Differential Pressure Scanner
Simultaneously samples static pressure taps along converging and diverging nozzle walls.
Electro-Pneumatic Pressure Regulator
Maintains constant stagnation pressure P_0 within +/- 0.5% during supersonic blowdown runs.
Optical Z-Schlieren Visualization Rig
Visualizes internal shock wave structures, expansion fans, and boundary layer separation.
Digital Data Acquisition System
Converts static-to-total pressure ratios into local isentropic Mach numbers along the duct.
FOLLOW THE METHOD
A reason behind every step.
Validate the isentropic area-Mach number relation (A/A*) in a supersonic de Laval nozzle and determine supersonic Mach expansion across nozzle area ratios. Standardized parameter settings: 1.2, 1.4, 1.68, 2.0, 2.4, 2.97 dimensionless.
01
Nozzle Pre-Run Inspection
Inspect the nozzle throat and divergent duct for moisture or particulate contamination and lock quartz optical windows.
02
Reservoir Charging and Stagnation Stabilization
Charge the reservoir to 8.0 bar and set the regulator to maintain stagnation total pressure P_0 = 500 kPa.
03
Throat Choking Verification
Initiate blowdown flow and verify that the throat static pressure ratio drops to P*/P_0 = 0.528, confirming sonic choking (M = 1).
04
Divergent Tap Pressure Acquisition
Acquire static pressures at divergent stations corresponding to A/A* = 1.20, 1.40, 1.68, 2.00, 2.40, and 2.97.
05
Isentropic Mach Number Computation
Compute local Mach numbers from the isentropic relation: M = sqrt(5 * [(P_0/P)^(2/7) - 1]) for air (gamma = 1.4).
06
Mach-Area Linear Regression
Plot (M - 1.0) versus (A/A* - 1.0), perform linear regression to determine the supersonic expansion gradient, and verify isentropic flow.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Supersonic de Laval Nozzle mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
(M - 1.0) \approx m \cdot \left(\frac{A}{A^*} - 1.0\right) + b
| # | Nozzle Area Ratio A/A* (dimensionless) | Supersonic Mach Number M (dimensionless) | Area Ratio Increment (A/A* - 1.0) | Mach Increment (M - 1.0) | Remove |
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