Linear Compressor Blade Cascade Wind Tunnel
Continuously running cascade tunnel with adjustable inlet guide vanes and boundary layer sidewall suction.
Aerospace & Aeronautical Engineering / Compressor Cascade Aerodynamics
FREE TO EXPLORELABORATORY 30 · AEROSPACE & AERONAUTICAL ENGINEERING
Axial Compressor Blade Cascade Aerodynamics and Diffusion Factor
Measure blade surface pressure distributions, exit flow turning angles theta_t, and Lieblein diffusion factor D across compressor blade cascades to determine stall margin. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
DIFFUSION FACTOR D—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with theta_t = 20.0 deg.
Adjust theta_t, 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 2D cascade neglects three-dimensional radial centrifugal forces, radial flow migration, and tip clearance leakage flows. Linear regression of the Lieblein diffusion factor against flow turning angle yields a sensitivity slope dD/dtheta_t = 0.0165 deg^-1 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
NACA 65-Series Compressor Blade Row (7 blades)
Precision airfoil cascade with chord c = 100 mm and adjustable solidity sigma = 1.25.
Multi-Channel Scanivalve Blade Surface Taps
Measures chordwise static pressures along suction and pressure surfaces of central blade.
Downstream 3-Hole Yaw-Pitch Aerodynamic Probe
Traverses 1.0 chord behind blade row to measure exit velocity V_2 and exit flow angle beta_2.
Automated Transverse Wake Traverse Rig
Maps total pressure wake deficit across three blade pitches to quantify cascade profile loss.
Digital Turbomachinery DAQ Workstation
Computes flow turning, diffusion factor D, and pressure rise coefficient C_p.
FOLLOW THE METHOD
A reason behind every step.
Measure blade surface pressure distributions, exit flow turning angles theta_t, and Lieblein diffusion factor D across compressor blade cascades to determine stall margin. Standardized parameter settings: 12.0, 16.0, 20.0, 25.0, 30.0, 35.0 deg.
01
Cascade Installation and Periodic Alignment
Install the 7-blade cascade, verifying uniform blade spacing s = 80 mm and adjusting inlet sidewall bleeds for pitchwise flow periodicity.
02
Wind Tunnel Speed Stabilization
Run tunnel to test inlet velocity V_1 = 50 m/s, stabilizing inlet dynamic pressure at q_1 = 1530 Pa.
03
Inlet Flow Angle Calibration
Adjust inlet guide vanes to set initial flow turning angle to theta_t = 12.0 degrees, measuring blade surface C_p distributions.
04
Systematic Turning Angle Stepping
Step the turning angle through theta_t = 16.0, 20.0, 25.0, 30.0, and 35.0 degrees, recording surface pressures and exit wake profiles.
05
Diffusion Factor Computation
Calculate velocity ratio V_2 / V_1 and tangential velocity turning Delta V_theta to compute Lieblein diffusion factor D.
06
Diffusion Factor Linear Regression
Plot D versus theta_t, perform linear regression to determine turning sensitivity dD / dtheta_t, and pinpoint the stall limit D_crit = 0.58.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Compressor Cascade Aerodynamics mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
D \approx m \cdot \theta_{t,\text{deg}} + b
| # | Blade Flow Turning Angle theta_t (deg) | Diffusion Factor D (dimensionless) | Flow Turning Angle theta_t (deg) | Lieblein Diffusion Factor D | Remove |
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