BASELINE PERFORMANCE ASSESSMENT OF A LOCALLY FABRICATED MICRO-JET ENGINE

In pursuit of indigenous technological capability in aerospace propulsion, this paper presents the design, development, and operational testing of a small-scale jet engine targeting a nominal thrust output of 250 N. The primary objective was to demonstrate the mechanical workability, aerodynamic integration, and structural integrity of locally fabricated components under operational run conditions. Experimental validation was conducted using a dedicated static test rig to evaluate ignition characteristics, rotational stability, and thermal performance during baseline runs. Test results confirmed the functional viability of the integrated turbomachinery assembly, establishing essential baseline datasets regarding mass flow efficiency, rotor dynamics, and thrust output. These empirical findings provide a benchmark for future iterative design improvements, particularly in turbine thermal tolerance and combustion efficiency.