E-11 - Google Sheets

	A	B	C	D	E	F	G	H	I	J	K	L	M
1	Density	Density	MaxGTOW	Thrust	Flat Plate	Thrust	Convert	Convert	Convert		Convert	Convert
2	(Sea Level)	(50,000 ft)	(lbs)	fwd (lbs)	Cd	fwd (m/s²)	m/s² to G	km/h to kts	kgs to lbs		m to ft	m² to ft²
3	0.002377	0.000361	524,000	700,419	1.35	13.108	9.80665	0.5405405405	2.2046		3.2808	10.7636
4
5	Pitch Section	Dh (m)	MAC	Span (m)	Arm (ft)	Pht (Vv)	Elevator m²	Elevator ft²			Rotational	Available
6		27.946484	#REF!	#REF!	91.68682471	#REF!	22.004120	236.8446			0	72,058
7
8	Yaw Section	Dv (m)	Dw (m)	Critical	Arm (ft)	Pvt (Vh)	Rudder m²	Rudder ft²		Torque lb-m	Torque lb-ft	Required
9		26.842907	15.407158	61.6921632	88.06620929	#REF!	12.181351	131.1158		4,214,651	13,827,426	157,012
10
11	Roll Section	Arm (m)	Arm (ft)			Aileron m²	Aileron m²	Aileron ft²			Flap m²	Flap ft²
12		13.132276	43.08437			43.813049	21.9065245	235.7941			0	0.0000
13
14	Lift Section	Pitch Arm	Area m²	Area ft²	Cl (T/O)	Cx (T/O)	Lift	at T/O	Cl (mcp)	Cx (mcp)	Lift	at mcp
15	Wing VCl	6.826286	384.02847	4133.55	0.350000	1.719452	524,000	pounds	0.373646	0.278779	524,000	pounds
16	H-Stabilizer	27.946484	178.70	1923.44	0.059648	0.136356	41,554	pounds	-0.375000	-0.130193	-244,714	pounds
17	V-Stabilizer	n/a	91.46	984.41	n/a	n/a	n/a		n/a	n/a	n/a
18
19	Drag Section		Area m²	Area ft²	Cd (T/O)	Cx (T/O)	Drag	at T/O	Cd (mcp)	Cx (mcp)	Drag	at mcp
20	Frontal Drag	Total	n/a	n/a	n/a	2.442910	744,472	pounds	n/a	0.372638	700,419	pounds
21	Wing Derived	Top Down	426.92474	4595.27	0.004038	0.022051	6,720	pounds	0.006000	0.004977	9,354	pounds
22	Vert Stab Drag	Side	0.00000	0.00	0.005500	0.00000000	0	pounds	0.006000	0.000000	0	pounds
23	Horz Stab Drag	Top Down	0.00000	0.00	0.005500	0.000000	0	pounds	0.006000	0.000000	0	pounds
24	Engine Intakes	Frontal	15.94375	171.61	1.350000	0.275349	83,912	pounds	1.350000	0.041818	78,602	pounds
25	Landing Struts	Frontal	2.837112	30.54	1.350000	0.048997	14,932	pounds	1.350000	0.007441	13,987	pounds
26	Frontal Drag	Frontal	140.17709	1508.82	1.350000	2.420859	2,903,809	pounds	1.350000	0.367661	691,064	pounds
27	Flat Plate Bottom		825.59845	8886.45	1.350000	14.258089	n/a		n/a	n/a	n/a
28	Flat Plate Sides		287.31705	3092.58	1.350000	4.961967	n/a		n/a	n/a	n/a
29
30
31	Airfoils	Options	Effective	YZ Radian	Cl (Max)	Cd (Max)	AOI	Cl (T/O)	Cd (T/O)	AOA	Cl mcp	Cd mcp
32	64A410	NACA	95.7%	0.294001	1.5750	1.3500	+0.000°	0.350000	0.004250	-3.000°	0.373646	0.006000
33	w/ Winglets	5%	95.7%	0.294001	1.5750	1.2825	+0.000°	0.350000	0.004038	-3.000°	0.373646	0.005700
34
35			Qty.						MAC X m
36	Wing Pylon			this works with load limits section below but WTH					0.0
37	Wing Strut								0.0
38	Wing Shroud								0.0
39
40	Airfoils	Options			Cl (Max)	Cd (Max)	AOI	Cl (T/O)	Cd (T/O)	AOA	Cl mcp	Cd mcp
41	63A010	NACA			0.8400	1.3500	2.292°	0.059648	0.005500	-0.708°	-0.375000	0.006000
42
43		VCL m²	HCL m²	Qty.		VCL ft²		HCL ft²	MAC m	Yaw Arm	Pitch Arm	Roll Arm
44	Tail Shroud					0.0		0.0	12.0	21.7	6.4	21.3
45	Tail Fin					0.0		0.0	???	13.3	8.3	10.8
46
47	Engines	Area m²	Qty.	Z Area m²	Cd	Power Ea.	XZ Radian	XZ DCM m	Yaw Arm	YZ Radian	YZ DCM m	Pitch Arm
48	Critical Engine	5.314582	2	10.6	16.18418	33.256%	1.0338856	4.1	18.80400	0.158412	12.5	-0.38014
49	Tail Engine	5.314582	1	5.3	8.09209	33.488%	0.0000000	0.0	0.00000	0.106246	37.7	-0.38014
50
51	Velocity	(fps)	(m/s)	(km/s)	(km/h)	(kts)	(mph)		P-moment	P-moment	Legend
52	Vs0	1095.215	334	0.334	1202	650
53	Vref	1423.779	434	0.434	1562	844
54	Vs1	260.234	79	0.079	286	154	177		2415680	10415858	Label	TESTS
55	Vmc	1095.215	334	0.334	1202	650	747	PWR:DRAG			Descriptor
56	Vr	552.040	168	0.168	606	327	376	Vmc+5%:Vr			Provided	Makeship
57	V2	1204.736	367	0.367	1322	715	821	TODO?
58	Vc (MSL)	535.458	163	0.163	588	318	365	0.48			Calculated	Viewscreen
59	Vc (50,000 ft)	1370.994	418	0.418	1504	813	935	1.58			Constant
60	Mach (50,000 ft)	869.700	265	0.265	954	516	593	1.00
61	Mach (MSL)	1,116.400	340	0.340	1225	662	761	1.00
62	Limit (10,000 ft)	421.492	128	0.128	463	250	287
63				vvv	vvv			vvv	vvv	vvv	vvv
64	Symmetric	Area m²	Area ft²	Cx	Arm m		Aymmetric	m² at m	Cd ft² at m	m² at m	Cd ft² at m
65	Roll Drag	825.59845	8886.451634	14.25808948	4.597237		Yaw Drag	514.301758	8.88199401	2427.452881	41.92212376		these are significantly lower
66							Pitch Drag	1508.846313	26.0577836	3854.561035	66.56828893		yaw should be profile drag
67								Body less tail		Tail section			weighted at Y(XZ) arm
68													pitch is plan drag
69	Published Ceiling	Modulate									VP Ceiling		weighted at Y(XZ) arm
70	(km)										(km)		same thing with roll arm
71	0	1.6633									0		about half as much
72
73
74
75
76	Vertical Down	11689.334	201.87
77
78	Design Limits	Category	Positive J	Positive J	Positive J	Positive J		Negative J	Negative J	Negative J	Negative J
79	Wings	Utility	Lower G	Lower lbs	Ultimate G	Ultimate lbs		Lower G	Lower lbs	Ultimate G	Ultimate lbs
80			4.4	#DIV/0!	6.6	#DIV/0!	#DIV/0!	-1.8	#DIV/0!	-2.7	#DIV/0!
81
82
83
84
85
86
87	Thermodynamics	Crit Sfc Temp	700	K
88	Absorption	Emission
89	#VALUE!	#VALUE!