Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-I (root) (supermarine371i-il) Reynolds number: 100,000 Max Cl/Cd: 46.75 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371i-il-100000.txt Download as CSV file: xf-supermarine371i-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-I (root)
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3861 0.12898 0.12420 -0.0251 1.0000 0.1244
-12.500 -0.4028 0.12611 0.12137 -0.0284 1.0000 0.1288
-12.250 -0.4406 0.12266 0.11802 -0.0340 1.0000 0.1301
-12.000 -0.3971 0.11785 0.11313 -0.0305 1.0000 0.1327
-11.750 -0.3856 0.11474 0.11002 -0.0304 1.0000 0.1375
-11.500 -0.4000 0.11073 0.10604 -0.0332 1.0000 0.1429
-11.250 -0.4440 0.10519 0.10061 -0.0394 1.0000 0.1445
-11.000 -0.3958 0.10235 0.09771 -0.0349 1.0000 0.1489
-10.750 -0.3941 0.09851 0.09388 -0.0357 1.0000 0.1528
-10.500 -0.4436 0.09166 0.08718 -0.0420 1.0000 0.1598
-10.250 -0.4145 0.08871 0.08418 -0.0396 1.0000 0.1623
-10.000 -0.5736 0.05884 0.05413 -0.0589 1.0000 0.0855
-9.750 -0.5980 0.05449 0.04973 -0.0577 1.0000 0.0834
-9.500 -0.6975 0.06299 0.05785 -0.0496 1.0000 0.0856
-9.250 -0.7210 0.06093 0.05578 -0.0443 1.0000 0.0836
-9.000 -0.7524 0.05949 0.05427 -0.0374 1.0000 0.0818
-8.750 -0.8031 0.05623 0.05045 -0.0284 1.0000 0.0755
-8.500 -0.8091 0.05343 0.04755 -0.0248 1.0000 0.0741
-8.250 -0.8174 0.05046 0.04434 -0.0208 1.0000 0.0724
-8.000 -0.8251 0.04710 0.04061 -0.0167 1.0000 0.0705
-7.750 -0.8274 0.04402 0.03713 -0.0130 1.0000 0.0697
-7.500 -0.8237 0.04151 0.03427 -0.0099 1.0000 0.0702
-7.250 -0.8148 0.03904 0.03142 -0.0075 0.9995 0.0709
-7.000 -0.7924 0.03599 0.02787 -0.0072 0.9964 0.0710
-6.750 -0.7661 0.03347 0.02491 -0.0074 0.9936 0.0717
-6.500 -0.7404 0.03151 0.02258 -0.0072 0.9906 0.0739
-6.250 -0.7140 0.02993 0.02066 -0.0072 0.9880 0.0775
-6.000 -0.6865 0.02883 0.01958 -0.0077 0.9855 0.0818
-5.750 -0.6566 0.02773 0.01826 -0.0081 0.9834 0.0869
-5.500 -0.6326 0.02675 0.01732 -0.0079 0.9810 0.0939
-5.250 -0.6084 0.02586 0.01633 -0.0074 0.9780 0.1039
-5.000 -0.5841 0.02476 0.01530 -0.0072 0.9753 0.1180
-4.750 -0.5632 0.02351 0.01428 -0.0065 0.9729 0.1422
-4.500 -0.5451 0.02223 0.01343 -0.0055 0.9708 0.1907
-4.250 -0.5304 0.02134 0.01291 -0.0038 0.9685 0.2485
-4.000 -0.5207 0.02019 0.01248 -0.0013 0.9655 0.3502
-3.750 -0.5186 0.01929 0.01319 0.0043 0.9629 0.6100
-3.500 -0.5040 0.01980 0.01368 0.0076 0.9607 0.7087
-3.250 -0.4838 0.02049 0.01431 0.0101 0.9582 0.7529
-3.000 -0.4620 0.02132 0.01506 0.0125 0.9557 0.7881
-2.750 -0.4496 0.02182 0.01551 0.0165 0.9536 0.8128
-2.500 -0.4350 0.02227 0.01587 0.0199 0.9510 0.8356
-2.250 -0.4140 0.02279 0.01629 0.0222 0.9483 0.8554
-2.000 -0.3882 0.02330 0.01668 0.0232 0.9458 0.8734
-1.750 -0.3527 0.02401 0.01727 0.0224 0.9430 0.8925
-1.500 -0.3035 0.02493 0.01805 0.0191 0.9406 0.9106
-1.250 -0.2371 0.02591 0.01888 0.0122 0.9382 0.9259
-1.000 -0.1558 0.02667 0.01947 0.0018 0.9360 0.9328
-0.750 -0.1135 0.02696 0.01968 -0.0018 0.9326 0.9421
-0.500 -0.0458 0.02740 0.02001 -0.0101 0.9300 0.9497
-0.250 0.0052 0.02772 0.02027 -0.0154 0.9270 0.9569
0.000 0.0469 0.02786 0.02038 -0.0192 0.9229 0.9638
0.250 0.0860 0.02804 0.02054 -0.0225 0.9182 0.9714
0.500 0.1533 0.02824 0.02073 -0.0310 0.9151 0.9806
0.750 0.2231 0.02832 0.02083 -0.0400 0.9122 0.9877
1.000 0.2536 0.02847 0.02102 -0.0419 0.9059 0.9940
1.250 0.3034 0.02848 0.02106 -0.0473 0.9004 0.9985
1.500 0.3442 0.02856 0.02120 -0.0506 0.8939 1.0000
1.750 0.3654 0.02868 0.02137 -0.0503 0.8845 1.0000
2.000 0.3850 0.02885 0.02159 -0.0496 0.8746 1.0000
2.250 0.4330 0.02875 0.02159 -0.0536 0.8674 1.0000
2.500 0.4401 0.02903 0.02193 -0.0507 0.8559 1.0000
2.750 0.4818 0.02888 0.02188 -0.0533 0.8461 1.0000
3.000 0.5600 0.02787 0.02106 -0.0613 0.8366 1.0000
3.250 0.5853 0.02758 0.02088 -0.0605 0.8231 1.0000
3.500 0.6307 0.02642 0.01986 -0.0619 0.8081 1.0000
3.750 0.6665 0.02528 0.01886 -0.0615 0.7929 1.0000
4.000 0.6920 0.02446 0.01817 -0.0597 0.7785 1.0000
4.250 0.7181 0.02339 0.01721 -0.0576 0.7631 1.0000
4.500 0.7425 0.02219 0.01615 -0.0551 0.7465 1.0000
4.750 0.7668 0.02085 0.01491 -0.0523 0.7285 1.0000
5.000 0.7823 0.01996 0.01413 -0.0488 0.7073 1.0000
5.250 0.8010 0.01873 0.01301 -0.0453 0.6809 1.0000
5.500 0.8062 0.01822 0.01263 -0.0406 0.6438 1.0000
5.750 0.8110 0.01761 0.01202 -0.0356 0.5791 1.0000
6.000 0.8154 0.01744 0.01081 -0.0295 0.4266 1.0000
6.250 0.8000 0.01853 0.01122 -0.0224 0.3345 1.0000
6.500 0.7834 0.01949 0.01169 -0.0152 0.2738 1.0000
6.750 0.7706 0.02043 0.01220 -0.0087 0.2288 1.0000
7.000 0.7667 0.02149 0.01290 -0.0037 0.1907 1.0000
7.250 0.7705 0.02264 0.01377 0.0000 0.1614 1.0000
7.500 0.7800 0.02393 0.01475 0.0026 0.1393 1.0000
7.750 0.7958 0.02519 0.01592 0.0043 0.1206 1.0000
8.000 0.8165 0.02659 0.01723 0.0053 0.1060 1.0000
8.250 0.8442 0.02833 0.01885 0.0051 0.0947 1.0000
8.500 0.8685 0.02977 0.02028 0.0055 0.0860 1.0000
8.750 0.8997 0.03196 0.02264 0.0050 0.0800 1.0000
9.000 0.9233 0.03367 0.02447 0.0055 0.0749 1.0000
9.250 0.9497 0.03638 0.02722 0.0052 0.0706 1.0000
9.500 0.9658 0.03859 0.02988 0.0070 0.0686 1.0000
9.750 0.9797 0.04121 0.03289 0.0088 0.0670 1.0000
10.000 0.9897 0.04375 0.03577 0.0109 0.0652 1.0000
10.250 1.0001 0.04603 0.03825 0.0127 0.0631 1.0000
10.500 1.0135 0.04865 0.04095 0.0138 0.0612 1.0000
10.750 1.0142 0.05192 0.04460 0.0165 0.0612 1.0000
11.000 0.9981 0.05541 0.04860 0.0209 0.0621 1.0000
11.250 0.9710 0.05901 0.05263 0.0260 0.0635 1.0000
11.500 0.9448 0.06289 0.05681 0.0297 0.0647 1.0000
11.750 0.9186 0.06709 0.06126 0.0321 0.0657 1.0000
12.000 0.8931 0.07165 0.06602 0.0332 0.0669 1.0000
12.250 0.8659 0.07678 0.07132 0.0332 0.0679 1.0000
12.500 0.8436 0.08223 0.07688 0.0322 0.0691 1.0000
12.750 0.8293 0.08806 0.08278 0.0308 0.0702 1.0000
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