Thermal scheme	C	N	K	Mode of thermal flow
Horizontally located cylinder	0,54	0,25	1	Laminar flow
	0,1	0,33	1	Turbulent flow
Vertical surface and vertically located cylinder with a big diameter D in relation to the length L	0,8	0,25		Laminar flow For obtaining of Nu is used : C=0,6; X=x;
	0,0246	0,4		Turbulent flow For obtaining of Nu is used : C=0.0296; X=x;
Vertically located cylinder with not big diameter D in relation to the length L	0,686	0,25		Laminar flow
Horizontal surface. Thermal flow is directed upward	0.54	0,25	1	Laminar flow
	0.14	0.33	1	Turbulent flow
Horizontal surface. Thermal flow is directed downward	0.27	0.25	1	Only for laminar flow
Sloped surface	0,8	0,25		Laminar flow (Gr is multiplied by cos Φ in the formula of the vertical lamina)
Sphere	0,49	0,25	1	Laminar flow (air)
Two vertical laminae with different temperatures	0.04	1		Air layer
Vertically located thick cylinder	0,01	1		Air column
Two vertically located surfaces. (the upper is hotter)	-	-	-	Ideal conditions:
	0.27	0.25	1	Laminar flow (air) 3.10^5< Gr.Pr<3.10^10
Two vertically located surfaces. (the lower is hotter)	0,195	0.25	Pr^-0,25	Laminar flow (air) 10^4< Gr <4.10^5
	0.068	0.33	Pr^-0,25	Turbulent flow (air) Gr>4.10^5
Two parallel vertical surfaces with different temperatures (equal a)	0,18	0.25		Laminar flow (air) 2.10^4< Gr<4.10^5
	0.065	0.33		Turbulent flow (air) 2.10^5<Gr<10^7
Two parallel sloped surfaces				Nuv – vertical direction Nuv – horizontal direction
Two co-axis cylinders	0,317	0,25		Laminar flow
Two concentric spheres	0,61	0.25		Laminar flow

T,[K]	r, [kg/m^3]	Cp, J/kg.K	m, [kg/(m.s)]	l, [W/m.K]	Pr	b,[K^-1]
100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 850 900 950 1000 1100 1200 1300 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300 2400 2500	3.601 2.3675 1.7684 1.4128 1.1774 0.998 0.8826 0.7833 0.7048 0.6423 0.5879 0.543 0.503 0.4709 0.4405 0.4149 0.3925 0.3716 0.3524 0.3204 0.2947 0.2707 0.2515 0.2355 0.2211 0.2082 0.197 0.1858 0.1762 0.1682 0.1602 0.1538 0.1458 0.1394	1027 1010 1006 1005 1006 1009 1014 1021 1030 1039 1055 1064 1075 1086 1098 1110 1121 1132 1142 1160 1179 1197 1214 1230 1248 1267 1287 1309 1338 1372 1419 1482 1574 1688	0.000006924 0.000010283 0.000013289 0.00001488 0.00001983 0.00002075 0.00002286 0.00002484 0.00002671 0.00002848 0.00003018 0.00003177 0.00003332 0.00003481 0.00003625 0.00003765 0.00003899 0.00004023 0.00004152 0.0000444 0.0000469 0.0000493 0.0000517 0.000054 0.0000563 0.0000585 0.0000607 0.0000629 0.000065 0.0000672 0.0000693 0.0000714 0.0000735 0.0000757	0.00925 0.01374 0.01809 0.02227 0.02624 0.03003 0.03365 0.03707 0.04038 0.04360 0.04659 0.04953 0.0523 0.05509 0.05779 0.06028 0.06279 0.06525 0.06752 0.0732 0.0782 0.0837 0.0891 0.0946 0.1 0.105 0.111 0.177 0.124 0.131 0.139 0.149 0.161 0.175	0.77 0.753 0.739 0.722 0.708 0.697 0.689 0.683 0.680 0.680 0.680 0.682 0.684 0.686 0.689 0.692 0.696 0.699 0.702 0.704 0.707 0.705 0.705 0.705 0.705 0.705 0.704 0.704 0.702 0.7 0.707 0.71 0.718 0.73	0.01 0.00667 0.005 0.004 0.00333 0.00286 0.0025 0.00222 0.002 0.00182 0.00167 0.00154 0.00143 0.00133 0.00125 0.00118 0.00111 0.00105 0.001 0.000909 0.000833 0.000769 0.000714 0.000667 0.000625 0.000588 0.000556 0.000526 0.0005 0.000476 0.000454 0.000435 0.000417 0.0004