Low-Speed Smoke Wind Tunnel
Optical wind tunnel test section with anti-reflective glass walls and ultra-low turbulence intensity.
Aerospace & Aeronautical Engineering / Smoke Flow Separation
FREE TO EXPLORELABORATORY 09 · AEROSPACE & AERONAUTICAL ENGINEERING
Boundary Layer Flow Separation and Smoke-Wire Visualization
Quantify the chordwise flow separation point x_sep / c on an airfoil as angle of attack increases toward stall using smoke-wire optical flow visualization. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
SEPARATED CHORD FRACTION—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with alpha - 6.0 = 4.0 deg.
Adjust alpha - 6.0, 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
Smoke-wire flow visualization is restricted to low Reynolds numbers (Re_c < 2.0 x 10^5) to maintain distinct streaklines. Linear regression of the separated chord fraction against angle of attack yields a forward migration rate of 0.0650 deg^-1 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Pulsed Nichrome Smoke-Wire System
0.1 mm diameter nichrome wire coated with specialized paraffin oil, energized with high-voltage pulse.
High-Speed CMOS Digital Camera
Captures 1000 fps flow visualization imagery with high-resolution macro optics.
NACA 0012 Matt-Black Airfoil Model
Non-reflective chord model (c = 150 mm) with fine chordwise grid markings for optical spatial calibration.
Synchronized LED Strobe Illumination
High-intensity pulsed light sheet provides sharp optical contrast for smoke streaklines.
Digital Image Processing Workstation
Executes edge detection and velocity field tracking to identify the exact separation point x_sep.
FOLLOW THE METHOD
A reason behind every step.
Quantify the chordwise flow separation point x_sep / c on an airfoil as angle of attack increases toward stall using smoke-wire optical flow visualization. Standardized parameter settings: 2.0, 4.0, 6.0, 8.0, 10.0, 12.0 deg.
01
Optical Calibration and Scale Setting
Position high-speed camera perpendicular to test section window and calibrate pixels-per-millimeter using model chord markings.
02
Smoke-Wire Preparation
Apply uniform coating of mineral oil along vertical nichrome wire using an automated wiper carriage and align wire 50 mm upstream of leading edge.
03
Wind Tunnel Flow Initialization
Establish stable low-speed airflow at V_inf = 12 m/s to ensure clean laminar smoke streakline visibility without premature turbulent dispersion.
04
Angle of Attack Sweep and Pulse Triggering
Set angle of attack to alpha = 8.0, 10.0, 12.0, 14.0, 16.0, and 18.0 degrees, firing the smoke pulse and camera synchronously.
05
Separation Point Identification
Analyze image sequence to locate where smoke streaklines detach from the surface and reverse flow vortices originate, logging x_sep / c.
06
Separation Migration Analysis
Plot separated fraction (1 - x_sep / c) versus alpha, perform linear regression to determine separation migration rate, and identify critical stall angle.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Smoke Flow Separation mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
\left(1 - \frac{x_{\text{sep}}}{c}\right) = m \cdot (\alpha - \alpha_0) + b
| # | Angle of Attack Increment (deg) | Separated Chord Fraction (dimensionless) | Effective Angle of Attack Increment alpha - 6.0 (deg) | Separated Flow Fraction 1 - x_sep/c | Remove |
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