Complete Aircraft Model with Vertical Fin
Wind tunnel model (b = 600 mm) with modular vertical tail surfaces and geometric wing dihedral.
Aerospace & Aeronautical Engineering / Directional & Lateral Stability
FREE TO EXPLORELABORATORY 24 · AEROSPACE & AERONAUTICAL ENGINEERING
Lateral-Directional Weathercock Stability and Dihedral Effect
Measure yawing moment derivative C_n_beta (weathercock stability) and rolling moment derivative C_l_beta (dihedral effect) across a wind tunnel sideslip sweep. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
YAWING MOMENT C_N X 10^3—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with beta = 4.0 deg.
Adjust beta, 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
Linear derivative C_n_beta is valid for attached flow on the vertical fin (beta < 12 deg); high sideslip causes vertical fin stall. Linear regression of yawing moment coefficient against sideslip angle yields a weathercock derivative C_n_beta x 10^3 = 1.8000 deg^-1 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Precision Computerized Yaw Turntable
Rotates model in yaw from beta = -15 to +15 degrees with 0.02 degree angular resolution.
6-Component Internal Strain-Gauge Balance
Simultaneously measures yawing moment N, rolling moment L_roll, and side force Y.
Subsonic Wind Tunnel Test Section
Maintains uniform airspeed V_inf = 30.0 m/s with low free-stream turbulence intensity.
Dynamic Pressure Sensor
Monitors free-stream dynamic pressure q_inf to normalize moments into non-dimensional coefficients.
Digital Lateral-Directional DAQ Workstation
Calculates C_n and C_l and extracts stability derivatives C_n_beta and C_l_beta.
FOLLOW THE METHOD
A reason behind every step.
Measure yawing moment derivative C_n_beta (weathercock stability) and rolling moment derivative C_l_beta (dihedral effect) across a wind tunnel sideslip sweep. Standardized parameter settings: 1.0, 3.0, 5.0, 7.0, 8.5, 10.0 deg.
01
Balance Taring in Zero Sideslip
Align model symmetrically with tunnel axis (beta = 0 deg) and perform wind-off tare across all six balance channels.
02
Wind Tunnel Speed Stabilization
Run the wind tunnel to V_inf = 30 m/s, stabilizing dynamic pressure at q_inf = 551 Pa.
03
Zero-Sideslip Symmetry Check
Verify that measured side force Y, yawing moment N, and rolling moment L_roll are zero within balance noise at beta = 0 deg.
04
Systematic Sideslip Angle Sweep
Rotate the turntable through beta = 1.0, 3.0, 5.0, 7.0, 8.5, and 10.0 degrees, sampling 2000 points per channel at each step.
05
Coefficient Normalization
Compute non-dimensional yawing moment coefficient C_n = N / (q_inf * S * b) and rolling moment coefficient C_l = L_roll / (q_inf * S * b).
06
Weathercock Derivative Linear Regression
Plot C_n x 10^3 versus beta, perform linear regression to determine the weathercock derivative C_n_beta, and verify positive stability.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Directional & Lateral Stability mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
C_n = C_{n\beta} \cdot \beta \implies C_n \times 10^3 = m \cdot \beta_{\text{deg}} + b
| # | Sideslip Angle beta (deg) | Yawing Moment C_n x 10^3 (dimensionless) | Sideslip Angle beta (deg) | Yawing Moment Coefficient C_n x 10^3 | Remove |
|---|
No readings yet. Execute an aerodynamic trial and record it.
Calculate it yourself.
CHECK YOUR UNDERSTANDING