12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 100,000 Max Cl/Cd: 34.77 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk-il-100000.txt Download as CSV file: xf-joukowsk-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: 12% JOUKOWSKI AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8105 0.09726 0.09199 0.0055 1.0000 0.0929
-11.750 -0.8146 0.09158 0.08632 0.0032 1.0000 0.0938
-11.500 -1.0325 0.06111 0.05494 -0.0191 1.0000 0.0806
-11.250 -1.0434 0.05632 0.04993 -0.0189 1.0000 0.0812
-11.000 -1.0371 0.05296 0.04651 -0.0186 1.0000 0.0827
-10.750 -1.0269 0.05037 0.04384 -0.0181 1.0000 0.0845
-10.500 -1.0219 0.04754 0.04078 -0.0174 1.0000 0.0867
-10.250 -1.0193 0.04429 0.03712 -0.0165 1.0000 0.0892
-10.000 -1.0153 0.04113 0.03335 -0.0154 1.0000 0.0916
-9.750 -0.9993 0.03823 0.03033 -0.0150 1.0000 0.0945
-9.500 -0.9794 0.03663 0.02868 -0.0145 1.0000 0.0987
-9.250 -0.9632 0.03458 0.02622 -0.0136 1.0000 0.1034
-9.000 -0.9427 0.03241 0.02398 -0.0131 1.0000 0.1078
-8.750 -0.9212 0.03104 0.02250 -0.0126 1.0000 0.1139
-8.500 -0.9001 0.02922 0.02047 -0.0120 1.0000 0.1202
-8.250 -0.8769 0.02801 0.01926 -0.0115 1.0000 0.1277
-8.000 -0.8540 0.02655 0.01775 -0.0110 1.0000 0.1360
-7.750 -0.8311 0.02548 0.01645 -0.0104 1.0000 0.1460
-7.500 -0.8071 0.02430 0.01544 -0.0100 1.0000 0.1567
-7.250 -0.7833 0.02321 0.01439 -0.0095 1.0000 0.1689
-7.000 -0.7594 0.02223 0.01343 -0.0090 1.0000 0.1829
-6.750 -0.7354 0.02133 0.01257 -0.0085 1.0000 0.1987
-6.500 -0.7113 0.02051 0.01180 -0.0080 1.0000 0.2164
-6.250 -0.6871 0.01978 0.01107 -0.0075 1.0000 0.2366
-6.000 -0.6627 0.01906 0.01046 -0.0070 1.0000 0.2571
-5.750 -0.6383 0.01845 0.00999 -0.0064 1.0000 0.2790
-5.500 -0.6136 0.01791 0.00945 -0.0059 1.0000 0.3033
-5.250 -0.5891 0.01740 0.00911 -0.0053 1.0000 0.3260
-5.000 -0.5643 0.01697 0.00870 -0.0048 1.0000 0.3515
-4.750 -0.5397 0.01655 0.00846 -0.0041 1.0000 0.3745
-4.500 -0.5152 0.01619 0.00816 -0.0035 1.0000 0.3996
-4.250 -0.4911 0.01585 0.00796 -0.0027 1.0000 0.4228
-4.000 -0.4676 0.01556 0.00778 -0.0018 1.0000 0.4465
-3.750 -0.4450 0.01529 0.00758 -0.0008 1.0000 0.4701
-3.500 -0.4240 0.01505 0.00749 0.0004 1.0000 0.4916
-3.250 -0.4045 0.01485 0.00739 0.0018 1.0000 0.5138
-3.000 -0.3867 0.01470 0.00729 0.0034 1.0000 0.5361
-2.750 -0.3703 0.01459 0.00731 0.0051 1.0000 0.5561
-2.500 -0.3546 0.01455 0.00738 0.0067 1.0000 0.5765
-2.250 -0.3243 0.01460 0.00750 0.0056 0.9935 0.6017
-2.000 -0.2717 0.01466 0.00771 0.0010 0.9761 0.6295
-1.750 -0.2181 0.01469 0.00784 -0.0037 0.9601 0.6580
-1.500 -0.1685 0.01470 0.00796 -0.0071 0.9432 0.6838
-1.250 -0.1260 0.01470 0.00801 -0.0091 0.9242 0.7085
-1.000 -0.0933 0.01471 0.00811 -0.0088 0.9018 0.7299
-0.750 -0.0653 0.01473 0.00816 -0.0075 0.8799 0.7512
-0.500 -0.0416 0.01474 0.00818 -0.0054 0.8583 0.7729
-0.250 -0.0205 0.01475 0.00822 -0.0029 0.8354 0.7938
0.000 0.0000 0.01475 0.00823 0.0000 0.8140 0.8140
0.250 0.0205 0.01475 0.00822 0.0029 0.7938 0.8354
0.500 0.0415 0.01474 0.00818 0.0054 0.7729 0.8584
0.750 0.0653 0.01473 0.00816 0.0075 0.7512 0.8799
1.000 0.0933 0.01471 0.00811 0.0088 0.7299 0.9018
1.250 0.1260 0.01469 0.00801 0.0091 0.7085 0.9242
1.500 0.1685 0.01471 0.00796 0.0071 0.6838 0.9432
1.750 0.2181 0.01469 0.00784 0.0037 0.6581 0.9601
2.000 0.2717 0.01466 0.00771 -0.0010 0.6296 0.9761
2.250 0.3243 0.01459 0.00750 -0.0056 0.6017 0.9935
2.500 0.3546 0.01455 0.00738 -0.0067 0.5765 1.0000
2.750 0.3702 0.01459 0.00731 -0.0051 0.5560 1.0000
3.000 0.3866 0.01470 0.00729 -0.0034 0.5362 1.0000
3.250 0.4045 0.01485 0.00739 -0.0018 0.5138 1.0000
3.500 0.4239 0.01505 0.00749 -0.0004 0.4917 1.0000
3.750 0.4450 0.01529 0.00758 0.0008 0.4701 1.0000
4.000 0.4676 0.01556 0.00778 0.0018 0.4465 1.0000
4.250 0.4911 0.01585 0.00796 0.0027 0.4228 1.0000
4.500 0.5152 0.01619 0.00816 0.0035 0.3996 1.0000
4.750 0.5398 0.01655 0.00846 0.0041 0.3745 1.0000
5.000 0.5643 0.01697 0.00870 0.0048 0.3515 1.0000
5.250 0.5891 0.01740 0.00911 0.0053 0.3260 1.0000
5.500 0.6136 0.01791 0.00945 0.0059 0.3033 1.0000
5.750 0.6383 0.01845 0.00999 0.0065 0.2790 1.0000
6.000 0.6627 0.01906 0.01046 0.0070 0.2571 1.0000
6.250 0.6870 0.01978 0.01108 0.0075 0.2366 1.0000
6.500 0.7113 0.02051 0.01180 0.0080 0.2164 1.0000
6.750 0.7354 0.02133 0.01257 0.0085 0.1987 1.0000
7.000 0.7594 0.02222 0.01343 0.0090 0.1829 1.0000
7.250 0.7833 0.02321 0.01439 0.0095 0.1688 1.0000
7.500 0.8070 0.02430 0.01544 0.0100 0.1567 1.0000
7.750 0.8311 0.02548 0.01644 0.0104 0.1460 1.0000
8.000 0.8540 0.02655 0.01774 0.0110 0.1360 1.0000
8.250 0.8769 0.02800 0.01925 0.0115 0.1277 1.0000
8.500 0.9000 0.02922 0.02047 0.0120 0.1202 1.0000
8.750 0.9212 0.03104 0.02251 0.0126 0.1139 1.0000
9.000 0.9427 0.03241 0.02398 0.0131 0.1079 1.0000
9.250 0.9632 0.03458 0.02622 0.0136 0.1033 1.0000
9.500 0.9794 0.03663 0.02868 0.0145 0.0987 1.0000
9.750 0.9993 0.03823 0.03033 0.0150 0.0945 1.0000
10.000 1.0153 0.04114 0.03336 0.0154 0.0915 1.0000
10.250 1.0193 0.04428 0.03711 0.0165 0.0891 1.0000
10.500 1.0220 0.04752 0.04075 0.0174 0.0867 1.0000
10.750 1.0272 0.05034 0.04379 0.0181 0.0844 1.0000
11.000 1.0382 0.05285 0.04637 0.0186 0.0825 1.0000
11.250 1.0447 0.05633 0.04993 0.0189 0.0810 1.0000
11.500 1.0319 0.06107 0.05491 0.0192 0.0805 1.0000
11.750 1.0072 0.06545 0.05952 0.0196 0.0806 1.0000
12.000 0.6972 0.13784 0.13250 -0.0296 0.1607 1.0000
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Polar data table (+)
Polar graphs
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