Experimental and thermodynamic analyses of a two-stroke UAV engine operated with gasoline–methanol blends

This study delineates experimental investigations and thermodynamic analyses conducted on a two-cylinder, two-stroke, air-cooled engine-standard for uncrewed aerial vehicles (UAVs)-oper ated with various gasoline–methanol fuel blends. Performance and emission metrics were ob tained at five thrust levels (5, 10, 15, 20, and 26 kg) utilizing five distinct fuel blends (M0, M10, M20, M30, and M40). The acquired data facilitated comprehensive evaluations of energy, exergy, and sustainability. At lower thrust levels, the minimal fuel consumption was observed with M0; at higher thrust levels, the minimum was recorded with M40. An increase in the methanol content within the fuel blends resulted in a notable reduction in CO2 emissions; for instance, at a thrust of 26 kg, CO2 emissions were 5.65% for M0 and 3.91% for M40. The highest efficiencies in terms of energy and exergy were achieved at a thrust of 15 kg across all fuel blends. Correspondingly, the maximum sustainability index was determined to be 1.39 for M40 at a thrust of 15 kg.