NACA 0012 Precision Wind Tunnel Model
CNC-machined aluminum wing section of 150 mm chord with 32 flush-mounted surface static pressure taps.
Aerospace & Aeronautical Engineering / NACA 0012 Pressure Distribution
FREE TO EXPLORELABORATORY 02 · AEROSPACE & AERONAUTICAL ENGINEERING
Surface Pressure Distribution and Normal Force on a Symmetric Airfoil (NACA 0012)
Measure chordwise static pressure distributions C_p(x/c) over a NACA 0012 symmetric airfoil across angles of attack and integrate surface pressures to determine the section normal force coefficient slope dC_n/dalpha. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
NORMAL FORCE COEFFICIENT C_N—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with alpha = 4.0 deg.
Adjust alpha, 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
Two-dimensional wing model spans entire test section, but sidewall boundary layer interactions induce slight corner flow separation. Linear regression of the integrated normal force coefficient across alpha yields a slope of 0.1097 deg^-1 matching thin airfoil theory with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Multi-Channel Scanivalve Pressure Scanner
Simultaneously acquires differential static pressures from 32 taps with 16-bit A/D conversion at 500 Hz.
Automated Rotary Turntable Mount
Positions airfoil angle of attack with optical shaft encoder resolution of 0.02 degrees.
Subsonic Wind Tunnel Test Section
Maintains uniform airspeed V_inf = 35 m/s corresponding to chord Reynolds number Re_c = 3.6 x 10^5.
Pitot-Static Reference Probe
Monitors free-stream dynamic pressure q_inf upstream of the airfoil model induction zone.
Digital Data Acquisition Workstation
Computes chordwise C_p distributions and executes real-time numerical integration for normal force.
FOLLOW THE METHOD
A reason behind every step.
Measure chordwise static pressure distributions C_p(x/c) over a NACA 0012 symmetric airfoil across angles of attack and integrate surface pressures to determine the section normal force coefficient slope dC_n/dalpha. Standardized parameter settings: 0.0, 2.0, 4.0, 6.0, 8.0, 10.0 deg.
01
Model Alignment and Tap Leak Testing
Mount the NACA 0012 model horizontally between tunnel sidewalls, align chord line with tunnel axis (alpha = 0 deg), and verify zero pneumatic leakage across all 32 taps.
02
Wind Tunnel Baseline Initialization
Start the wind tunnel and stabilize free-stream velocity at V_inf = 35 m/s, recording reference static and dynamic pressures.
03
Zero-Lift Pressure Verification
Record baseline static pressure distributions at alpha = 0 deg, confirming identical upper and lower surface C_p curves and zero integrated normal force.
04
Angle of Attack Incrementation
Rotate the model through alpha = 2.0, 4.0, 6.0, 8.0, and 10.0 degrees, allowing 20 seconds at each setting for pressure transducer settling.
05
C_p Distribution Computation
Convert raw tap voltages to pressure coefficients C_p(x/c) across all 32 chord stations for both suction and pressure surfaces.
06
Trapezoidal Normal Force Integration
Execute numerical integration of (C_p,lower - C_p,upper) d(x/c) to calculate total section normal force coefficient C_n.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates NACA 0012 Pressure Distribution mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
C_n = 2\pi \alpha_{\text{rad}} \implies C_n = m \cdot \alpha_{\text{deg}} + b
| # | Angle of Attack alpha (deg) | Normal Force Coefficient C_n (dimensionless) | Angle of Attack alpha (deg) | Normal Force Coefficient C_n | Remove |
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