ULTIMATE (ultimate-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: ULTIMATE (ultimate-il) Reynolds number: 100,000 Max Cl/Cd: 38.96 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ultimate-il-100000.txt Download as CSV file: xf-ultimate-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: ULTIMATE
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 -0.7981 0.09191 0.08700 -0.0189 1.0000 0.0717
-11.750 -0.8129 0.08522 0.08027 -0.0219 1.0000 0.0702
-11.500 -0.8422 0.07786 0.07279 -0.0256 1.0000 0.0681
-11.250 -0.8806 0.07117 0.06589 -0.0276 1.0000 0.0659
-11.000 -0.9327 0.06560 0.05990 -0.0253 1.0000 0.0634
-10.750 -0.9765 0.06397 0.05764 -0.0186 1.0000 0.0612
-10.500 -0.9739 0.05936 0.05282 -0.0172 1.0000 0.0602
-10.250 -0.9778 0.05553 0.04868 -0.0147 1.0000 0.0600
-10.000 -0.9799 0.05228 0.04504 -0.0118 1.0000 0.0602
-9.750 -0.9789 0.04943 0.04176 -0.0088 1.0000 0.0606
-9.500 -0.9733 0.04655 0.03842 -0.0061 1.0000 0.0609
-9.250 -0.9625 0.04326 0.03475 -0.0040 1.0000 0.0610
-9.000 -0.9473 0.03939 0.03054 -0.0026 1.0000 0.0615
-8.750 -0.9262 0.03603 0.02698 -0.0020 1.0000 0.0627
-8.500 -0.9047 0.03383 0.02470 -0.0014 1.0000 0.0656
-8.250 -0.8831 0.03205 0.02275 -0.0004 1.0000 0.0694
-8.000 -0.8592 0.03027 0.02067 0.0005 1.0000 0.0723
-7.750 -0.8324 0.02790 0.01837 0.0005 1.0000 0.0765
-7.500 -0.8108 0.02654 0.01700 0.0015 1.0000 0.0830
-7.250 -0.7905 0.02490 0.01542 0.0027 1.0000 0.0897
-7.000 -0.7728 0.02370 0.01418 0.0046 1.0000 0.0992
-6.750 -0.7598 0.02237 0.01298 0.0070 1.0000 0.1130
-6.500 -0.7517 0.02086 0.01174 0.0104 1.0000 0.1371
-6.250 -0.7539 0.01872 0.01045 0.0154 1.0000 0.2258
-6.000 -0.7541 0.01763 0.01003 0.0205 1.0000 0.3484
-5.750 -0.7447 0.01726 0.00979 0.0241 1.0000 0.4048
-5.500 -0.7326 0.01696 0.00957 0.0272 1.0000 0.4452
-5.250 -0.7190 0.01670 0.00933 0.0301 1.0000 0.4806
-5.000 -0.7047 0.01646 0.00915 0.0329 1.0000 0.5142
-4.750 -0.6902 0.01630 0.00911 0.0357 1.0000 0.5495
-4.500 -0.6759 0.01625 0.00917 0.0387 1.0000 0.5865
-4.250 -0.6601 0.01621 0.00920 0.0414 1.0000 0.6192
-4.000 -0.6412 0.01611 0.00913 0.0434 1.0000 0.6452
-3.750 -0.6223 0.01601 0.00903 0.0453 1.0000 0.6706
-3.500 -0.6030 0.01593 0.00897 0.0471 1.0000 0.6965
-3.250 -0.5823 0.01588 0.00897 0.0487 1.0000 0.7221
-3.000 -0.5621 0.01586 0.00895 0.0503 1.0000 0.7493
-2.750 -0.5419 0.01586 0.00899 0.0520 1.0000 0.7775
-2.500 -0.5206 0.01593 0.00908 0.0535 1.0000 0.8061
-2.250 -0.4964 0.01606 0.00923 0.0544 1.0000 0.8343
-2.000 -0.4684 0.01623 0.00941 0.0545 1.0000 0.8630
-1.750 -0.4310 0.01652 0.00967 0.0525 1.0000 0.8902
-1.500 -0.3850 0.01694 0.01003 0.0485 1.0000 0.9143
-1.250 -0.3106 0.01763 0.01062 0.0390 0.9952 0.9289
-1.000 -0.2313 0.01829 0.01118 0.0284 0.9901 0.9373
-0.750 -0.1549 0.01881 0.01162 0.0184 0.9847 0.9458
-0.500 -0.0834 0.01911 0.01188 0.0092 0.9766 0.9548
-0.250 -0.0084 0.01926 0.01201 -0.0007 0.9691 0.9613
0.000 0.0644 0.01923 0.01200 -0.0102 0.9614 0.9692
0.250 0.1316 0.01908 0.01189 -0.0185 0.9497 0.9766
0.500 0.1959 0.01880 0.01166 -0.0262 0.9363 0.9838
0.750 0.2538 0.01843 0.01137 -0.0324 0.9207 0.9916
1.000 0.3058 0.01800 0.01100 -0.0372 0.9035 0.9996
1.250 0.3250 0.01774 0.01076 -0.0358 0.8811 1.0000
1.500 0.3405 0.01753 0.01055 -0.0334 0.8598 1.0000
1.750 0.3557 0.01738 0.01038 -0.0310 0.8399 1.0000
2.000 0.3723 0.01726 0.01027 -0.0291 0.8187 1.0000
2.250 0.3887 0.01709 0.01010 -0.0269 0.7995 1.0000
2.500 0.4053 0.01688 0.00989 -0.0245 0.7811 1.0000
2.750 0.4234 0.01673 0.00975 -0.0226 0.7609 1.0000
3.000 0.4422 0.01659 0.00961 -0.0208 0.7417 1.0000
3.250 0.4618 0.01648 0.00950 -0.0190 0.7238 1.0000
3.500 0.4820 0.01643 0.00946 -0.0174 0.7065 1.0000
3.750 0.5026 0.01643 0.00946 -0.0158 0.6894 1.0000
4.000 0.5236 0.01650 0.00957 -0.0144 0.6694 1.0000
4.250 0.5433 0.01643 0.00944 -0.0122 0.6445 1.0000
4.500 0.5623 0.01629 0.00922 -0.0097 0.6114 1.0000
4.750 0.5817 0.01620 0.00909 -0.0076 0.5732 1.0000
5.000 0.6022 0.01621 0.00904 -0.0058 0.5375 1.0000
5.250 0.6228 0.01629 0.00912 -0.0042 0.4956 1.0000
5.500 0.6420 0.01648 0.00919 -0.0023 0.4338 1.0000
5.750 0.6493 0.01830 0.00968 0.0007 0.2016 1.0000
6.000 0.6592 0.02063 0.01119 0.0030 0.1186 1.0000
6.250 0.6750 0.02193 0.01237 0.0049 0.1006 1.0000
6.500 0.6912 0.02325 0.01357 0.0068 0.0913 1.0000
6.750 0.7103 0.02446 0.01482 0.0085 0.0841 1.0000
7.000 0.7297 0.02612 0.01627 0.0097 0.0776 1.0000
7.250 0.7530 0.02757 0.01784 0.0109 0.0744 1.0000
7.500 0.7761 0.02911 0.01950 0.0119 0.0709 1.0000
7.750 0.7981 0.03081 0.02121 0.0128 0.0668 1.0000
8.000 0.8215 0.03386 0.02430 0.0134 0.0645 1.0000
8.250 0.8414 0.03601 0.02680 0.0149 0.0639 1.0000
8.500 0.8593 0.03859 0.02975 0.0165 0.0636 1.0000
8.750 0.8737 0.04128 0.03285 0.0184 0.0632 1.0000
9.000 0.8847 0.04398 0.03597 0.0206 0.0624 1.0000
9.250 0.8922 0.04703 0.03943 0.0229 0.0620 1.0000
9.500 0.8977 0.05079 0.04355 0.0251 0.0628 1.0000
9.750 0.9036 0.05558 0.04853 0.0267 0.0641 1.0000
10.000 0.8766 0.05978 0.05368 0.0321 0.0704 1.0000
10.250 0.8617 0.06486 0.05901 0.0345 0.0741 1.0000
10.500 0.8230 0.07029 0.06482 0.0381 0.0816 1.0000
10.750 0.7797 0.06299 0.05753 0.0432 0.0780 1.0000
11.000 0.7386 0.06637 0.06109 0.0460 0.0783 1.0000
11.250 0.6948 0.07156 0.06643 0.0456 0.0785 1.0000
11.500 0.6426 0.07944 0.07444 0.0420 0.0788 1.0000
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Polar data table (+)
Polar graphs
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