2-DOF Aeroelastic Airfoil Rig
Rigid NACA 0012 section (c = 200 mm) mounted on external linear plunge springs and torsional flexure pivots.
Aerospace & Aeronautical Engineering / 2-DOF Airfoil Flutter
FREE TO EXPLORELABORATORY 40 · AEROSPACE & AERONAUTICAL ENGINEERING
Classical 2-DOF Airfoil Flutter (Coupled Pitch-Plunge Aeroelasticity)
Measure coupled plunge displacement h(t) and pitch angle alpha(t) of an elastically mounted airfoil to detect frequency coalescence and the flutter boundary V_flutter. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
FREQUENCY METRIC DELTA(OMEGA^2)—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with V_inf^2 = 1200.0 m^2/s^2.
Adjust V_inf^2, 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
2-DOF pitch-plunge model assumes rigid 2D airfoil sections; real aircraft wings experience 3D spanwise bending and control surface flutter. Linear regression of the frequency separation metric against airspeed squared yields a coalescence slope k_f = 0.0450 rad^2/m^2 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Non-Contact Laser Displacement Sensors
Twin triangulation lasers measuring plunge displacement h(t) and pitch rotation alpha(t) at 5 kHz.
Subsonic Aeroelastic Wind Tunnel
Provides smooth airspeed control from V_inf = 15 to 55 m/s with automatic emergency brake doors.
Electrodynamic Modal Shaker Actuator
Provides initial impulse excitation to measure modal frequencies and damping ratios across airspeeds.
Fast Fourier Transform (FFT) Modal Analyzer
Computes real-time cross-spectral density and tracks pitch/plunge peak frequencies.
Automated Flutter Suppression Damper
Electromagnetic safety brake that clamps model motion instantly upon flutter onset.
FOLLOW THE METHOD
A reason behind every step.
Measure coupled plunge displacement h(t) and pitch angle alpha(t) of an elastically mounted airfoil to detect frequency coalescence and the flutter boundary V_flutter. Standardized parameter settings: 500.0, 800.0, 1200.0, 1600.0, 2000.0, 2400.0 m^2/s^2.
01
Zero-Wind Modal Benchmarking
With wind tunnel off (V_inf = 0), pluck the model to record baseline plunge frequency omega_h0 = 18.85 rad/s (3.0 Hz) and pitch frequency omega_alpha0 = 31.42 rad/s (5.0 Hz).
02
Low-Speed Flow Initialization
Start wind tunnel at V_inf = 22.36 m/s (V_inf^2 = 500 m^2/s^2), apply small impulse, and acquire h(t) and alpha(t) time series.
03
Systematic Airspeed Stepping
Step airspeed through V_inf^2 = 800, 1200, 1600, 2000, and 2400 m^2/s^2 (V_inf up to 49.0 m/s).
04
Modal Frequency Extraction
Compute FFT power spectrum at each speed, tracking the convergence of the two modal frequency peaks.
05
Frequency Separation Calculation
Calculate squared frequency separation Delta(omega^2) = |omega_alpha^2 - omega_h^2| at each velocity setting.
06
Coalescence Linear Regression
Plot Delta(omega^2) versus V_inf^2, perform linear regression to determine coalescence slope k_f = 0.0450, and extrapolate the flutter speed V_flutter.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates 2-DOF Airfoil Flutter mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
\Delta(\omega^2) = \Delta\omega_0^2 - k_f \cdot V_\infty^2 \implies \Delta(\omega^2) = -m \cdot (V_\infty^2) + b
| # | Airspeed Squared V_inf^2 (m^2/s^2) | Frequency Metric Delta(omega^2) (rad^2/s^2) | Airspeed Squared V_inf^2 (m^2/s^2) | Frequency Separation Metric Delta(omega^2) (rad^2/s^2) | Remove |
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