NACA 23012 Airfoil with 25% Plain Flap
Precision aluminum wing model (c = 200 mm) with a hinged trailing-edge flap (c_f = 50 mm).
Aerospace & Aeronautical Engineering / High-Lift Flap Deflection
FREE TO EXPLORELABORATORY 08 · AEROSPACE & AERONAUTICAL ENGINEERING
Aerodynamic Lift Augmentation via Trailing-Edge Flap Deflection
Measure lift coefficient increments Delta C_L and hinge moment variations as a function of plain and slotted trailing-edge flap deflection angles delta_f. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
LIFT INCREMENT DELTA C_L—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with delta_f = 10.0 deg.
Adjust delta_f, 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
Plain flap effectiveness decreases above delta_f = 20 deg due to boundary layer separation on the flap suction surface. Linear regression of Delta C_L against delta_f yields a flap effectiveness slope dC_L/ddelta_f = 0.0580 deg^-1 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Digital Servo Actuator & Angle Encoder
Sets flap deflection angle from 0 to 35 degrees with 0.1 degree repeatability.
Multi-Component Wind Tunnel Balance
Measures total lift, drag, and pitching moment as flap angle is modulated.
Internal Strain-Gauge Hinge Moment Sensor
Measures aerodynamic hinge torque required to hold the flap deflected against oncoming flow.
Subsonic Wind Tunnel Test Section
Maintains uniform airspeed V_inf = 30 m/s corresponding to chord Reynolds number Re_c = 4.1 x 10^5.
Digital Data Acquisition System
Records aerodynamic coefficients and performs real-time flap effectiveness regression.
FOLLOW THE METHOD
A reason behind every step.
Measure lift coefficient increments Delta C_L and hinge moment variations as a function of plain and slotted trailing-edge flap deflection angles delta_f. Standardized parameter settings: 5.0, 10.0, 15.0, 20.0, 25.0, 30.0 deg.
01
Flap Zero Alignment
Set the flap deflection angle to zero (delta_f = 0 deg) flush with the main airfoil contour and lock the model pitch at alpha = 4.0 degrees.
02
Wind Tunnel Stabilization
Power the wind tunnel to V_inf = 30 m/s, stabilizing dynamic pressure at q_inf = 551 Pa, and record the clean baseline lift coefficient C_L,clean.
03
Systematic Flap Deflection
Step the flap angle through delta_f = 5.0, 10.0, 15.0, 20.0, 25.0, and 30.0 degrees using the calibrated servo actuator.
04
Lift and Hinge Moment Acquisition
Sample 2000 data points at each flap angle to measure total lift C_L, calculating Delta C_L = C_L - C_L,clean, and log hinge moment C_h.
05
Flow Visualization Check
Observe tufts on the flap upper surface to monitor trailing-edge flow separation development at large flap deflections.
06
Flap Effectiveness Regression
Plot Delta C_L versus delta_f in the linear pre-separation regime, extracting the flap effectiveness parameter dC_L / ddelta_f.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates High-Lift Flap Deflection mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
\Delta C_L = \tau a_0 \delta_f \implies \Delta C_L = m \cdot \delta_{f,\text{deg}} + b
| # | Flap Deflection Angle delta_f (deg) | Lift Increment Delta C_L (dimensionless) | Flap Deflection Angle delta_f (deg) | Lift Coefficient Increment Delta C_L | Remove |
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