Modular Wing Set (AR = 2 to 8)
Interchangeable rectangular wings of chord c = 100 mm with spans from 200 mm to 800 mm.
Aerospace & Aeronautical Engineering / Finite Wing Induced Drag
FREE TO EXPLORELABORATORY 07 · AEROSPACE & AERONAUTICAL ENGINEERING
Finite Wing Aspect Ratio Effects and Induced Downwash
Investigate wingtip vortex downwash and quantify induced drag coefficient C_Di as a function of reciprocal aspect ratio 1/AR using Prandtl's classical lifting-line theory. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
INDUCED DRAG COEFFICIENT C_DI—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with 1/AR = 0.2 dimensionless.
Adjust 1/AR, 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
Prandtl lifting-line theory assumes unswept, high-aspect-ratio wings (AR > 4.0); small non-linearities appear at AR = 2.0. Linear regression of C_Di against 1/AR yields a slope of 0.1348 matching the Prandtl lifting-line theoretical gradient with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
External 3-Component Wind Tunnel Balance
Measures total aerodynamic lift and drag forces with 0.05 N accuracy.
Miniature 5-Hole Downwash Probe
Traverses the trailing vortex field to directly map the local downwash velocity vector w(y).
Automated Model Pitch Turntable
Trims each wing to maintain an exact constant lift coefficient C_L = 0.60.
Dynamic Pressure Sensor
Monitors free-stream dynamic pressure q_inf at constant test airspeed V_inf = 30 m/s.
Laser Sheet Particle Flow Visualizer
Illuminates wingtip vortex core diameter, circulation, and trajectory behind each wingtip.
FOLLOW THE METHOD
A reason behind every step.
Investigate wingtip vortex downwash and quantify induced drag coefficient C_Di as a function of reciprocal aspect ratio 1/AR using Prandtl's classical lifting-line theory. Standardized parameter settings: 0.125, 0.167, 0.2, 0.25, 0.333, 0.5 dimensionless.
01
Wing Model Mounting and Taring
Mount the baseline AR = 8.0 wing on the external balance, perform wind-off weight tares, and verify aerodynamic zero.
02
Wind Tunnel Stabilization
Accelerate wind tunnel airflow to V_inf = 30 m/s and trim angle of attack to achieve C_L = 0.60.
03
Drag Subtraction for Induced Drag
Measure total drag C_D, subtract the profile drag C_D0 measured on the 2D airfoil model, isolating induced drag C_Di.
04
Aspect Ratio Variation Sweep
Repeat the test across modular wings with AR = 6.0, 5.0, 4.0, 3.0, and 2.0 (corresponding to 1/AR = 0.125 to 0.500).
05
Downwash Mapping
Traverse the 5-hole probe across the spanwise wake behind the AR = 4.0 wing to record local downwash angles.
06
Prandtl Lifting-Line Regression
Plot C_Di against 1/AR, perform linear regression to determine the slope m = C_L^2 / (pi * e), and extract Oswald efficiency factor e.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Finite Wing Induced Drag mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
C_{Di} = \frac{C_L^2}{\pi e} \cdot \frac{1}{AR} \implies C_{Di} = m \cdot \left(\frac{1}{AR}\right) + b
| # | Inverse Aspect Ratio 1/AR (dimensionless) | Induced Drag Coefficient C_Di (dimensionless) | Inverse Aspect Ratio 1/AR | Induced Drag Coefficient C_Di | Remove |
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