Theoretical Analysis and Experimental Researches regarding the Asymmetrical Fluid Flow Applied in Aeronautics

Table 2

Nr.crt	Static pressure [N/m^2]	[m/s]	Force [N]	[Nm]	[Nm]
1	101229,6367	4,122222	2,00683	0,03137	−0,00261
2	101229,7828	4,178888	2,02760	0,033470	−0,002413
3	101229,9896	4,210001	2,07610	0,035853	−0,000893
4	101230,0755	4,290344	2,10305	0,037589	0,000804
5	101230,3241	4,340777	2,13139	0,039402	0,00094
6	101230,7204	4,386788	2,15353	0,041249	0,00192
7	101231,0777	4,433453	2,17919	0,042487	0,00277
8	101231,4515	4,532223	2,21553	0,044657	0,00365
9	101232,0023	4,544555	2,22803	0,046067	0,00538