Wind Tunnel Propeller Test Rig
Rigid dynamometer nacelle holding an electric brushless motor and precision shaft torque sensor.
Aerospace & Aeronautical Engineering / Propeller Performance & Thrust
FREE TO EXPLORELABORATORY 27 · AEROSPACE & AERONAUTICAL ENGINEERING
Aircraft Propeller Momentum and Blade Element Aerodynamic Performance
Measure propeller thrust coefficient C_T, power coefficient C_P, and propulsive efficiency eta_p across advance ratios J = V / (n D) to evaluate blade element theory. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
THRUST DEFICIT C_T0 - C_T—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with J = 0.5 dimensionless.
Adjust J, 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
Blade Element Momentum Theory (BEMT) assumes steady axisymmetric inflow without blade tip vortex compressibility. Linear regression of the thrust coefficient deficit against advance ratio yields a slope dC_T/dJ = 0.1350 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Calibrated 2-Blade Aircraft Propeller (D = 300 mm)
Carbon-fiber Clark-Y twisted propeller model with fixed pitch ratio P/D = 0.80.
In-Line Optical Shaft Encoder & Tachometer
Measures propeller rotational speed n up to 6000 RPM with +/- 1 RPM accuracy.
Axial Thrust and Reaction Torque Load Cells
Simultaneously measures propeller thrust T (in N) and shaft torque Q (in N-m).
Subsonic Wind Tunnel Test Section
Delivers controllable airspeeds from 5 to 40 m/s to vary advance ratio J.
Digital Motor ESC & Telemetry DAQ
Maintains constant motor RPM while sampling aerodynamic thrust and electrical power.
FOLLOW THE METHOD
A reason behind every step.
Measure propeller thrust coefficient C_T, power coefficient C_P, and propulsive efficiency eta_p across advance ratios J = V / (n D) to evaluate blade element theory. Standardized parameter settings: 0.3, 0.4, 0.5, 0.6, 0.7, 0.8 dimensionless.
01
Propeller Static Tare Calibration
Set wind tunnel speed to zero, spin up propeller to static RPM, and verify static thrust coefficient C_T0 = 0.1250.
02
Rotational Speed Stabilization
Set motor speed to constant n = 50.0 rev/s (3000 RPM) using the closed-loop optical tachometer.
03
Wind Tunnel Airspeed Stepping
Step wind tunnel velocity through V_inf = 4.5, 6.0, 7.5, 9.0, 10.5, and 12.0 m/s (corresponding to J = 0.30 to 0.80).
04
Thrust and Torque Acquisition
Sample 3000 points of axial thrust T and torque Q at each advance ratio plateau.
05
Non-Dimensional Coefficient Computation
Calculate non-dimensional thrust coefficient C_T and power coefficient C_P, computing propulsive efficiency eta_p.
06
Propeller Slope Linear Regression
Plot thrust deficit (C_T0 - C_T) versus J, perform linear regression to determine slope dC_T / dJ, and find zero-thrust advance ratio J_0.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Propeller Performance & Thrust mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
(C_{T0} - C_T) = m \cdot J + b
| # | Advance Ratio J (dimensionless) | Thrust Deficit C_T0 - C_T (dimensionless) | Advance Ratio J = V_inf / (n*D) | Thrust Coefficient Deficit C_T0 - C_T | Remove |
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