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

Table 2

Results of the GT-power simulation when α = 10°.

α (°)	n (RPM)	λset	To (Nm)	Po (kw)	η	γ (RPM h/Kg)	Pc (MPa)
10	2500	12	9.551	2.501	0.177	2257.016	3.066
10	3000	12	7.352	2.310	0.175	2892.084	2.045
10	3500	12	7.195	3.633	0.189	2316.357	2.786
10	4000	12	8.874	3.717	0.185	2537.999	3.219
10	4500	12	14.272	6.725	0.204	1736.989	3.987
10	5000	12	10.635	5.568	0.194	2219.936	2.986
10	5500	12	6.053	3.486	0.163	3280.692	2.760
10	6000	12	5.634	3.539	0.156	3362.353	2.687