Laboratory Micro-Turbojet Engine Test Rig
Single-shaft gas turbine (thrust 150 N, max RPM 120,000) running Jet-A1 kerosene with digital FADEC.
Aerospace & Aeronautical Engineering / Turbojet Brayton Cycle
FREE TO EXPLORELABORATORY 28 · AEROSPACE & AERONAUTICAL ENGINEERING
Real Joule-Brayton Thermodynamic Cycle in Aircraft Gas Turbines
Measure compressor and turbine pressure ratios, stagnation temperatures, and thermal efficiency eta_th to evaluate real open Joule-Brayton cycle performance. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
SPECIFIC WORK W_C—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with x_pi = 0.8 dimensionless.
Adjust x_pi, 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
Combustion pressure loss (Delta P_b / P_03 approx 3-5%) introduces slight non-ideal deviation from isobaric combustion. Linear regression of specific compressor work against the pressure parameter yields a slope of 345.00 kJ/kg with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Multi-Point Stagnation Pressure Rake
Measures total pressures P_01, P_02, P_03, P_04, and P_05 across all thermodynamic stations.
Fast-Response K-Type Thermocouple Probes
Measures stagnation temperatures T_01 to T_05 with 0.5 K accuracy and ceramic radiation shields.
Digital Fuel Mass Flow Turbine Meter
Measures volumetric and mass fuel consumption rate m_dot_fuel with 0.1% accuracy.
Axial Thrust Load Cell Stand
Measures net engine reaction thrust F_net across throttle settings from idle to full power.
Thermodynamic Cycle DAQ Workstation
Constructs real-time Temperature-Entropy (T-s) and Pressure-Volume (P-v) cycle diagrams.
FOLLOW THE METHOD
A reason behind every step.
Measure compressor and turbine pressure ratios, stagnation temperatures, and thermal efficiency eta_th to evaluate real open Joule-Brayton cycle performance. Standardized parameter settings: 0.45, 0.6, 0.8, 1.0, 1.2, 1.4 dimensionless.
01
Engine Startup and Idle Stabilization
Initiate automated electric start sequence, spooling turbojet up to idle (35,000 RPM) and verifying fuel pressure.
02
Stationary Environmental Baseline
Record compressor face inlet stagnation pressure P_01 and temperature T_01 = 293.15 K.
03
Throttle Power Stepping
Advance engine throttle to establish compressor pressure parameters x = 0.45, 0.60, 0.80, 1.00, 1.20, and 1.40.
04
Cycle State Variable Acquisition
Record total pressures and temperatures at compressor exit (P_03, T_03) and turbine inlet/exit (T_04, T_05) at each plateau.
05
Compressor Work Computation
Compute actual specific work: w_c = c_p * (T_03 - T_01), and calculate isentropic efficiency eta_c.
06
Cycle Work Linear Regression
Plot specific work w_c versus pressure parameter x, perform linear regression to extract slope c_p*T_01/eta_c, and evaluate cycle efficiency.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Turbojet Brayton Cycle mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
w_c = \frac{c_p T_{01}}{\eta_c} \left(\pi_c^{\frac{\gamma-1}{\gamma}} - 1\right) \implies w_c = m \cdot x + b
| # | Compressor Pressure Parameter (dimensionless) | Specific Work w_c (kJ/kg) | Compressor Pressure Parameter pi_c^0.286 - 1 | Compressor Specific Work w_c (kJ/kg) | Remove |
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No readings yet. Execute an aerodynamic trial and record it.
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