Closed-Circuit Subsonic Wind Tunnel
Provides steady, low-turbulence airflow across a 0.5 m x 0.5 m test section with variable frequency fan drive.
Aerospace & Aeronautical Engineering / Wind Tunnel Calibration
FREE TO EXPLORELABORATORY 01 · AEROSPACE & AERONAUTICAL ENGINEERING
Subsonic Wind Tunnel Calibration and Dynamic Pressure Measurement
Calibrate the test-section velocity field of a closed-circuit subsonic wind tunnel and determine ambient air density by measuring dynamic pressure q across calibrated airspeed settings. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
DYNAMIC PRESSURE Q—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with V_inf = 20.0 m/s.
Adjust V_inf, 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
Incompressible Bernoulli formulation assumes Mach number remains below 0.3; at 60 m/s (M = 0.176), compressibility effects contribute < 0.8% error. The ordinary least-squares fit of dynamic pressure against velocity squared extracts the empirical air density with 99.999% fidelity to standard atmospheric conditions.
Aeronautical apparatus & wind tunnel sensors.
Standard NPL Pitot-Static Probe
Measures total and static pressures simultaneously along the central streamline without flow disturbance.
High-Precision Digital Micromanometer
Measures differential dynamic head with 0.1 Pa resolution and temperature-compensated silicon sensors.
Motor Frequency Inverter & Tachometer
Regulates axial fan impeller rotation speed from 200 to 2800 RPM with digital PID closed-loop control.
Digital Barometer & Platinum RTD Thermometer
Monitors ambient atmospheric pressure and air temperature to compute theoretical reference air density.
Two-Axis Traverse Mechanism
Positions the Pitot-static tube across the cross-sectional grid to inspect boundary layer blockage and flow uniformity.
FOLLOW THE METHOD
A reason behind every step.
Calibrate the test-section velocity field of a closed-circuit subsonic wind tunnel and determine ambient air density by measuring dynamic pressure q across calibrated airspeed settings. Standardized parameter settings: 15.0, 20.0, 30.0, 40.0, 50.0, 60.0 m/s.
01
Initial Ambient Benchmarking
Record the ambient barometric pressure, room temperature, and relative humidity to calculate baseline thermodynamic air density.
02
Probe Alignment and Zero Balancing
Mount the Pitot-static probe along the geometric center of the test section parallel to the tunnel axis and zero the differential micromanometer.
03
Drive Fan Spin-Up
Power the axial fan drive, setting the initial motor inverter frequency to establish a steady baseline airspeed of 15 m/s.
04
Differential Pressure Acquisition
Allow airflow to stabilize for 60 seconds, then record differential dynamic pressure Delta P across 1000 synchronized digital samples.
05
Systematic Velocity Stepping
Step the tunnel airspeed through 20, 30, 40, 50, and 60 m/s, recording the steady-state dynamic pressure at each velocity plateau.
06
Transverse Boundary Survey
Perform a transverse probe sweep toward the test section sidewalls to verify core flow uniformity within 0.5% dynamic head variation.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Wind Tunnel Calibration mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
q = \frac{1}{2}\rho V_\infty^2 \implies q = m \cdot (V_\infty^2) + b
| # | Free-stream Airspeed V_inf (m/s) | Dynamic Pressure q (Pa) | Velocity Squared V_inf^2 (m^2/s^2) | Dynamic Pressure q (Pa) | Remove |
|---|
No readings yet. Execute an aerodynamic trial and record it.
Calculate it yourself.
CHECK YOUR UNDERSTANDING