Supersonic Wind Tunnel (Mach 2.50)
Blowdown supersonic wind tunnel with optical test section providing steady M_1 = 2.50 airflow.
Aerospace & Aeronautical Engineering / Oblique Shock Polar
FREE TO EXPLORELABORATORY 13 · AEROSPACE & AERONAUTICAL ENGINEERING
Oblique Shock Wave Geometry and Wedge Flow Deflection
Determine the shock wave angle beta over supersonic compression wedges of varying deflection angles theta and validate the theta-beta-M oblique shock relation. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
SHOCK WAVE ANGLE BETA—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with theta = 10.0 deg.
Adjust theta, 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
Leading edge boundary layer displacement thickness slightly increases the effective deflection angle theta by ~0.3 degrees. Linear regression of the shock angle increment against deflection angle yields a slope of 1.2500 matching weak oblique shock theory with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Modular Sharp-Nosed Compression Wedge
Interchangeable steel wedge models with deflection angles theta from 5.0 to 17.5 degrees and tip radius < 0.05 mm.
Z-Type Toepler Schlieren Optical System
Features parabolic front-surface mirrors (f = 1.5 m) and horizontal knife-edge for density gradient visualization.
High-Resolution CMOS Optical Camera
Captures 4K digital Schlieren images of the oblique shock wave boundary and wedge vertex.
Digital Protractor and Image Analysis Suite
Measures shock wave angle beta relative to oncoming free-stream vector with 0.05 degree precision.
Static Surface Tap Array on Wedge Face
Measures post-shock static pressure P_2 to verify thermodynamic pressure jump across the wave.
FOLLOW THE METHOD
A reason behind every step.
Determine the shock wave angle beta over supersonic compression wedges of varying deflection angles theta and validate the theta-beta-M oblique shock relation. Standardized parameter settings: 5.0, 7.5, 10.0, 12.5, 15.0, 17.5 deg.
01
Wedge Installation and Alignment
Install the theta = 5.0 degree wedge model, aligning the bottom flat surface parallel to the tunnel axis using optical laser leveling.
02
Schlieren Optical Alignment
Adjust the Schlieren light source, parabolic mirrors, and knife-edge to achieve uniform grey background illumination across test section.
03
Supersonic Tunnel Firing
Open the supersonic tunnel main valve, stabilizing upstream Mach number at M_1 = 2.50 with stagnation pressure P_01 = 400 kPa.
04
Schlieren Image Capture
Trigger high-resolution digital image capture of the attached oblique shock wave originating from the wedge apex.
05
Deflection Angle Stepping
Repeat the test across modular wedges of theta = 7.5, 10.0, 12.5, 15.0, and 17.5 degrees, recording the optical shock angle beta.
06
Shock Polar Regression
Plot (beta - beta_0) versus theta, where beta_0 = arcsin(1/M_1) = 23.58 deg, perform linear regression to determine the deflection gradient, and compare with theta-beta-M theory.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Oblique Shock Polar mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
(\beta - \beta_0) \approx m \cdot \theta_{\text{deg}} + b
| # | Wedge Deflection Angle theta (deg) | Shock Wave Angle beta (deg) | Wedge Flow Deflection Angle theta (deg) | Shock Wave Angle Increment (beta - beta_0) (deg) | Remove |
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