Table IV DoE_2 sheet Day S Solar... | Emerald Publishing

Table IV

DoE_2 sheet

Day	S			Solar cell-specific mass	RFC specific energy		Airframe weight adjustment factor	Payload weight	Payload power		V	RFC
Unit	[m]	AR	Solar cell efficiency	[kg/m^2]	[Wh/kg]	Fuel cell efficiency		[kg]	[W]	Round trip efficiency	[m/s]	[kW h]	Power margin
830	35	8	0.19	0.6	470	0.6	1	40	360	0.42	11.74685	13.36489	−9.00711E−08
	35	12	0.19	0.6	470	0.6	1	40	360	0.42	11.5125	11.93373	−7.36469E−08
	35	16	0.19	0.6	470	0.6	1	40	360	0.42	11.3666	11.115	−9.38558E−08
	35	20	0.19	0.6	470	0.6	1	40	360	0.42	11.36108	10.67784	−5.91906E−08
	35	24	0.19	0.6	470	0.6	1	40	360	0.42	11.35564	10.44875	−4.41271E−08
	40	8	0.19	0.6	470	0.6	1	40	360	0.42	11.23979	13.31474	−8.80737E−08
	40	12	0.19	0.6	470	0.6	1	40	360	0.42	11.02285	11.95361	−8.76E−08
	40	16	0.19	0.6	470	0.6	1	40	360	0.42	10.96401	11.1653	−6.88E−08

Day	S			Solar cell-specific mass	RFC specific energy		Airframe weight adjustment factor	Payload weight	Payload power		V	RFC
Unit	[m]	AR	Solar cell efficiency	[kg/m^2]	[Wh/kg]	Fuel cell efficiency		[kg]	[W]	Round trip efficiency	[m/s]	[kW h]	Power margin
830	35	8	0.19	0.6	470	0.6	1	40	360	0.42	11.74685	13.36489	−9.00711E−08
	35	12	0.19	0.6	470	0.6	1	40	360	0.42	11.5125	11.93373	−7.36469E−08
	35	16	0.19	0.6	470	0.6	1	40	360	0.42	11.3666	11.115	−9.38558E−08
	35	20	0.19	0.6	470	0.6	1	40	360	0.42	11.36108	10.67784	−5.91906E−08
	35	24	0.19	0.6	470	0.6	1	40	360	0.42	11.35564	10.44875	−4.41271E−08
	40	8	0.19	0.6	470	0.6	1	40	360	0.42	11.23979	13.31474	−8.80737E−08
	40	12	0.19	0.6	470	0.6	1	40	360	0.42	11.02285	11.95361	−8.76E−08
	40	16	0.19	0.6	470	0.6	1	40	360	0.42	10.96401	11.1653	−6.88E−08

Power margin	Energy margin	Nighttime energy margin	Cruise CL margin	Empty weight	Solar cells	Motor + propeller	RFC system	Avionics	Payload	Total weight
				[kg]	[kg]	[kg]	[kg]	[kg]	[kg]	[kg]
−9.00711E−08	−0.124685797	−9.75272E−08	0.793895234	37.49831619	17.388	4.780036399	28.40694412	0	40	128.0732967
−7.36469E−08	0.019803028	−7.9234E−08	0.740191068	45.31545915	17.388	4.300476831	25.36502275	0	40	132.3689587
−9.38558E−08	0.119710426	−9.98539E−08	0.694063757	51.83138032	17.388	4.023559879	23.62483142	0	40	136.8677716
−5.91906E−08	0.179516047	−6.31616E−08	0.666074592	57.52408917	17.388	3.874815794	22.69564192	0	40	141.4825469
−4.41271E−08	0.212854739	−4.71504E−08	0.638442305	62.63648709	17.388	3.796868509	22.20871298	0	40	146.0300686
−8.80737E−08	0.052623709	−9.48347E−08	0.790867231	41.60346486	19.872	4.806289578	28.3003559	0	40	134.5821103
−8.76E−08	0.211271016	−9.35012E−08	0.733542366	50.27639382	19.872	4.343423327	25.40727986	0	40	139.899097
−6.88E−08	0.321140141	−7.27079E−08	0.696024964	57.50564904	19.872	4.073856748	23.73174032	0	40	145.1832461
−8.90E−08	0.386605889	−9.42E−08	0.668397198	63.82157029	19.872	3.928682093	22.83848616	0	40	150.4607385
−6.01E−08	0.421187899	−6.35E−08	0.639590685	69.49365077	19.872	3.856319624	22.39324263	0	40	155.615213
−7.70008E−08	0.224191978	−8.22739E−08	0.790873828	45.595939	22.356	4.848580273	28.34723835	0	40	141.1477576

Span	E_req	E_solar	Lift to drag ratio	Required power for flight	Lift Coefficient	Drag Coefficient	H_Tail area	V_Tail area
[m]	[Wh]	[Wh]	L/D	[W]	CL	CD	[m^2]	[m^2]
16.7332	25,456.7	39,945.32	28.3699604	696.2944132	0.706104766	0.02488917	3.843810122	0.981828124
20.4939	22,902.74	39,945.32	33.89558791	590.3211265	0.759808932	0.02241616	3.147636645	1.18596499
23.66432	21,427.98	39,945.32	38.60558669	529.1279233	0.805936243	0.020876156	2.732634692	1.358060329
26.45751	20,635.83	39,945.32	42.53009319	496.2583644	0.833925408	0.01960789	2.449423513	1.509679366
28.98275	20,220.71	39,945.32	45.45401753	479.0335291	0.861557695	0.018954489	2.240365706	1.646753454
17.88854	25,596.51	45,651.8	28.28891853	702.0958493	0.709132769	0.025067511	4.392925854	1.193762293