aerofoil_lab_data.xlsx

	A	B	C	D	E	F	G	H	I	J	K	L
1	Position	x/c	y/c	No flow	No flow	0	4	8	12	16	18	20
2	s	0	0	164.5	164.5	50	54	90	141	207	244	149
3	1	0.0125	-0.02841	165.5	165.5	143	196	266	344	418	442	206
4	2	0.025	-0.03922	166	166	172	226	285	338	390	406	202
5	3	0.05	-0.05332	168.5	168.5	196	238	280	317	351	379	205
6	4	0.075	-0.063	166	166	198	230	262	291	341	380	203
7	5	0.1	-0.07024	166	166	201	229	252	271	322	312	204
8	6	0.15	-0.08018	166	166	200	216	226	254	254	254	205
9	7	0.2	-0.08606	166.5	166.5	200	207	219	223	228	229	205
10	8	0.25	-0.08912	166.5	166.5	192	200	212	214	222	222	206
11	9	0.3	-0.09003	166	166	189	200	208	210	212	212	205
12	10	0.4	-0.08705	165.5	165.5	188	193	199	199	199	199	199
13	11	0.5	-0.07941	165	165	185	188	188	188	188	185	194
14	12	0.6	-0.06845	165.5	165.5	181	184	184	184	180	172	193
15	13	0.7	-0.05496	165.5	165.5	177	180	177	174	166	155	192
16	14	0.8	-0.03935	165.5	165.5	174	166	164	158	151	144	188
17	15_bottom	0.9	-0.02172	165	165	150	149	146	142	140	140	184
18	15_top	0.9	0.02172	166.5	166.5	152	160	161	154	142	140	181
19	14	0.8	0.03935	166	166	173	170	164	156	145	146	184
20	13	0.7	0.05496	164.5	164.5	172	170	166	154	150	149	180
21	12	0.6	0.06845	165.5	165.5	178	178	172	166	154	150	177
22	11	0.5	0.07941	165.5	165.5	183	182	176	165	150	145	177
23	10	0.4	0.08705	165	165	186	184	174	161	144	138	170
24	9	0.3	0.09003	165	165	188	184	170	152	134	125	162
25	8	0.25	0.08912	165.5	165.5	188	182	166	147	127	118	155
26	7	0.2	0.08606	164	164	186	177	160	140	118	109	146
27	6	0.15	0.08018	164	164	188	177	155	131	108	98	136
28	5	0.1	0.07024	164	164	192	172	145	118	93	82	122
29	4	0.075	0.063	164	164	186	166	134	105	80	70	109
30	3	0.05	0.05332	163	163	188	157	122	90	66	56	96
31	2	0.025	0.03922	157	157	164	128	90	62	46	42	74
32	1	0.0125	0.02841	153.5	153.5	146	92	60	48	44	47	66
33	s	0	0	164.5	164.5	50	54	90	141	207	244	149
34	q			151	151	52	49	49	48	44	42	67
35
36	T_ambient:	22.2	[°C]		Please do not modify the location of the values and just fill your values.
37	p_ambient:	1013.25	[hPa]		You can add more angle of attack.
38	theta:	11	degree
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