S1012 (s1012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1012 (s1012-il) Reynolds number: 200,000 Max Cl/Cd: 37.72 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1012-il-200000.txt Download as CSV file: xf-s1012-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S1012
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8614 0.08134 0.07723 -0.0404 1.0000 0.0428
-14.000 -0.8976 0.07243 0.06815 -0.0458 1.0000 0.0426
-13.750 -0.9300 0.06553 0.06103 -0.0488 1.0000 0.0424
-13.500 -0.9578 0.06010 0.05539 -0.0499 1.0000 0.0423
-13.250 -0.9846 0.05562 0.05065 -0.0495 1.0000 0.0425
-13.000 -1.0051 0.05194 0.04671 -0.0481 1.0000 0.0425
-12.750 -1.0239 0.04884 0.04333 -0.0458 1.0000 0.0427
-12.500 -1.0405 0.04561 0.03984 -0.0429 1.0000 0.0431
-12.250 -1.0401 0.04274 0.03688 -0.0413 1.0000 0.0441
-12.000 -1.0326 0.04157 0.03572 -0.0396 1.0000 0.0452
-11.750 -1.0289 0.04026 0.03432 -0.0372 1.0000 0.0464
-11.500 -1.0255 0.03867 0.03257 -0.0347 1.0000 0.0476
-11.250 -1.0212 0.03673 0.03037 -0.0323 1.0000 0.0489
-11.000 -1.0155 0.03488 0.02819 -0.0299 1.0000 0.0503
-10.750 -1.0080 0.03340 0.02639 -0.0275 1.0000 0.0515
-10.500 -0.9909 0.03123 0.02424 -0.0269 1.0000 0.0538
-10.250 -0.9766 0.03046 0.02345 -0.0253 1.0000 0.0560
-10.000 -0.9682 0.02964 0.02251 -0.0226 1.0000 0.0582
-9.750 -0.9704 0.02904 0.02175 -0.0177 1.0000 0.0598
-9.500 -0.9729 0.02852 0.02103 -0.0128 1.0000 0.0610
-9.250 -0.9645 0.02694 0.01939 -0.0101 1.0000 0.0633
-9.000 -0.9572 0.02641 0.01888 -0.0070 1.0000 0.0656
-8.750 -0.9488 0.02587 0.01826 -0.0040 1.0000 0.0682
-8.500 -0.9305 0.02529 0.01747 -0.0027 0.9987 0.0716
-8.250 -0.9032 0.02395 0.01613 -0.0034 0.9966 0.0758
-8.000 -0.8750 0.02340 0.01553 -0.0042 0.9942 0.0806
-7.750 -0.8486 0.02293 0.01484 -0.0043 0.9916 0.0846
-7.500 -0.8225 0.02184 0.01387 -0.0047 0.9894 0.0901
-7.250 -0.7943 0.02134 0.01327 -0.0052 0.9868 0.0958
-7.000 -0.7655 0.02049 0.01242 -0.0060 0.9848 0.1016
-6.750 -0.7363 0.02004 0.01195 -0.0068 0.9830 0.1084
-6.500 -0.7132 0.01941 0.01131 -0.0063 0.9806 0.1147
-6.250 -0.6911 0.01901 0.01091 -0.0057 0.9779 0.1219
-6.000 -0.6665 0.01846 0.01038 -0.0055 0.9754 0.1301
-5.750 -0.6386 0.01811 0.00999 -0.0059 0.9731 0.1400
-5.500 -0.6116 0.01759 0.00957 -0.0063 0.9712 0.1519
-5.250 -0.5855 0.01715 0.00919 -0.0065 0.9696 0.1648
-5.000 -0.5710 0.01680 0.00890 -0.0043 0.9662 0.1777
-4.750 -0.5504 0.01641 0.00861 -0.0033 0.9631 0.1958
-4.500 -0.5286 0.01601 0.00833 -0.0027 0.9608 0.2202
-4.250 -0.5048 0.01550 0.00806 -0.0025 0.9585 0.2569
-4.000 -0.4805 0.01486 0.00780 -0.0025 0.9565 0.3229
-3.750 -0.4735 0.01422 0.00762 0.0009 0.9530 0.4087
-3.500 -0.4672 0.01337 0.00750 0.0047 0.9490 0.5455
-3.250 -0.4509 0.01340 0.00831 0.0081 0.9464 0.7019
-3.000 -0.4246 0.01378 0.00866 0.0088 0.9438 0.7531
-2.750 -0.3945 0.01426 0.00912 0.0090 0.9419 0.7802
-2.500 -0.3792 0.01462 0.00945 0.0118 0.9382 0.7987
-2.250 -0.3604 0.01500 0.00982 0.0142 0.9344 0.8144
-2.000 -0.3340 0.01542 0.01023 0.0151 0.9313 0.8278
-1.750 -0.3036 0.01584 0.01062 0.0154 0.9288 0.8398
-1.500 -0.2692 0.01621 0.01096 0.0147 0.9266 0.8512
-1.250 -0.2597 0.01643 0.01116 0.0185 0.9206 0.8625
-1.000 -0.2300 0.01678 0.01150 0.0189 0.9168 0.8708
-0.750 -0.1961 0.01701 0.01170 0.0182 0.9134 0.8807
-0.500 -0.1452 0.01748 0.01217 0.0146 0.9117 0.8876
-0.250 -0.1313 0.01763 0.01232 0.0177 0.9041 0.8977
0.000 0.0000 0.01853 0.01324 0.0000 0.9066 0.9066
0.250 0.1310 0.01763 0.01233 -0.0176 0.8977 0.9041
0.500 0.1451 0.01748 0.01217 -0.0146 0.8876 0.9116
0.750 0.1958 0.01701 0.01171 -0.0181 0.8807 0.9134
1.000 0.2301 0.01677 0.01150 -0.0189 0.8708 0.9168
1.250 0.2600 0.01643 0.01116 -0.0186 0.8628 0.9206
1.500 0.2690 0.01621 0.01096 -0.0146 0.8512 0.9266
1.750 0.3036 0.01583 0.01061 -0.0153 0.8396 0.9288
2.000 0.3342 0.01543 0.01023 -0.0152 0.8280 0.9313
2.250 0.3603 0.01500 0.00981 -0.0141 0.8143 0.9344
2.500 0.3792 0.01462 0.00945 -0.0118 0.7987 0.9382
2.750 0.3945 0.01426 0.00912 -0.0089 0.7803 0.9419
3.000 0.4246 0.01378 0.00866 -0.0088 0.7533 0.9438
3.250 0.4508 0.01340 0.00832 -0.0081 0.7028 0.9464
3.500 0.4673 0.01336 0.00750 -0.0047 0.5471 0.9490
3.750 0.4735 0.01422 0.00761 -0.0009 0.4093 0.9530
4.000 0.4805 0.01486 0.00780 0.0025 0.3232 0.9565
4.250 0.5049 0.01550 0.00806 0.0025 0.2571 0.9585
4.500 0.5286 0.01601 0.00833 0.0027 0.2200 0.9608
4.750 0.5504 0.01641 0.00861 0.0033 0.1958 0.9632
5.000 0.5710 0.01680 0.00890 0.0043 0.1776 0.9662
5.250 0.5854 0.01715 0.00919 0.0065 0.1648 0.9696
5.500 0.6117 0.01758 0.00956 0.0063 0.1516 0.9713
5.750 0.6387 0.01811 0.00999 0.0059 0.1401 0.9731
6.000 0.6666 0.01846 0.01038 0.0055 0.1300 0.9754
6.250 0.6911 0.01901 0.01091 0.0057 0.1220 0.9779
6.500 0.7132 0.01941 0.01131 0.0063 0.1148 0.9806
6.750 0.7363 0.02004 0.01195 0.0068 0.1084 0.9830
7.000 0.7656 0.02048 0.01241 0.0060 0.1015 0.9848
7.250 0.7944 0.02133 0.01326 0.0052 0.0957 0.9868
7.500 0.8225 0.02182 0.01385 0.0047 0.0900 0.9895
7.750 0.8487 0.02293 0.01485 0.0043 0.0847 0.9916
8.000 0.8750 0.02337 0.01550 0.0041 0.0804 0.9942
8.250 0.9033 0.02395 0.01613 0.0034 0.0758 0.9966
8.500 0.9306 0.02530 0.01749 0.0027 0.0716 0.9987
8.750 0.9489 0.02589 0.01829 0.0040 0.0683 1.0000
9.000 0.9572 0.02641 0.01888 0.0070 0.0655 1.0000
9.250 0.9644 0.02693 0.01938 0.0101 0.0633 1.0000
9.500 0.9730 0.02853 0.02104 0.0128 0.0610 1.0000
9.750 0.9700 0.02900 0.02171 0.0178 0.0597 1.0000
10.000 0.9680 0.02962 0.02249 0.0226 0.0582 1.0000
10.250 0.9767 0.03046 0.02345 0.0253 0.0560 1.0000
10.500 0.9911 0.03120 0.02420 0.0268 0.0538 1.0000
10.750 1.0081 0.03346 0.02645 0.0274 0.0515 1.0000
11.000 1.0157 0.03488 0.02819 0.0299 0.0503 1.0000
11.250 1.0216 0.03677 0.03041 0.0323 0.0490 1.0000
11.500 1.0257 0.03870 0.03259 0.0347 0.0476 1.0000
11.750 1.0287 0.04034 0.03441 0.0372 0.0464 1.0000
12.000 1.0332 0.04155 0.03570 0.0395 0.0453 1.0000
12.250 1.0400 0.04281 0.03697 0.0412 0.0441 1.0000
12.500 1.0407 0.04555 0.03978 0.0429 0.0432 1.0000
12.750 1.0243 0.04885 0.04335 0.0457 0.0427 1.0000
13.000 1.0059 0.05191 0.04669 0.0480 0.0425 1.0000
13.250 0.9831 0.05566 0.05070 0.0495 0.0424 1.0000
13.500 0.9577 0.06023 0.05552 0.0498 0.0423 1.0000
13.750 0.9297 0.06565 0.06117 0.0487 0.0424 1.0000
14.000 0.8990 0.07243 0.06813 0.0458 0.0426 1.0000
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