Optimization of Fuel Injection Control System of Two-Stroke Aeroengine of UAV

Table 3

Results of the GT-power simulation when α = 40°.

α (°)	n (RPM)	λset	To (Nm)	Po (kw)	η	γ (RPM·h/Kg)	Pc (MPa)
40	2500	14.5	9.122	2.388	0.149	1987.442	3.142
40	3000	14.5	8.869	2.786	0.140	1918.287	2.308
40	3500	14.5	12.132	4.447	0.213	2134.503	3.228
40	4000	14.5	12.926	5.414	0.206	1934.364	3.806
40	4500	14.5	15.451	7.281	0.179	1410.437	4.054
40	5000	14.5	13.459	7.047	0.179	1621.358	3.952
40	5500	14.5	10.109	5.823	0.203	2445.253	3.660
40	6000	14.5	9.111	5.725	0.165	2201.615	3.128